COMBUSTION HOLE INSERT WITH INTEGRATED FILM RESTARTER

Abstract

An insert for combustion air holes in a liner wall of a combustion chamber is disclosed. The insert includes a body, a flange extending from the body, and a restarter jet. The restarter jet includes a restarter inlet and a slot. The restarter inlet is located in a radially outer surface of the flange. The slot extends across the flange and up a portion of the body to a restarter outlet location proximal an end surface of the body. The slot is configured to direct air entering the restarter inlet out of the slot at the restarter outlet location along a surface of the liner wall inside the combustion chamber.

Description

TECHNICAL FIELD

The present disclosure generally pertains to gas turbine engines, and is directed toward a combustion hole insert with an integrated film restarter for a combustion chamber of a gas turbine engine.

BACKGROUND

Gas turbine engines include compressor, combustor, and turbine sections. The combustor includes a combustion chamber where an air fuel mixture is combusted. Some of the combustion air may be supplied through combustion holes located in the walls that line the combustion chamber. These walls may be film cooled inside the combustion chamber by directing cooling air along the surface of the wall. The combustion holes and the combustion air flowing through the combustion holes may aerodynamically affect the cooling film.

U.S. Pat. No. 4,700,544 to R. Fucci discloses a refilmer for placing the film of cool air impeded by combustion/dilution air holes of a combustor for a gas turbine engine that includes a grommet with a lip extending axially in the combustion chamber. The outer side wall of the grommet is recessed in the area overlying the lip so that when assembled, it forms a gap with the liner exposing the lip to cool air for forming the film. Tabs on the cool air side prevent the grommet from falling into the combustion chamber. The aperture in the grommet is oriented to direct the combustion/dilution air stream at a relative angle to the flow of combustion products. Indexing surfaces on the grommet fixture locates the grommet to the liner prior to being welded into place.

The present disclosure is directed toward overcoming one or more of the problems discovered by the inventors or that is known in the art.

SUMMARY OF THE DISCLOSURE

An insert for a liner wall of a combustion chamber for a gas turbine engine is disclosed. In embodiments, the insert includes a body, a flange, and a restarter jet. The body has a cylindrical shape with an insert axis. The body includes a body outer surface, a combustor jet surface, and a body end surface. The body outer surface is a cylindrical surface that forms an outer surface of the body. The combustor jet surface is located radially inward from the body outer surface forming a jet for directing combustion air into the combustion chamber. The body end surface is located at an axial end of the body and adjacent to the body outer surface and the combustor jet surface.

The flange is located at an opposite end of the body relative to the body end surface. The flange includes a flange contact surface and a flange outer surface. The flange contact surface is adjacent the body outer surface. The flange contact surface has an annular shape. The flange outer surface is adjacent the flange contact surface. The flange outer surface has a cylindrical shape located radially outward from the body outer surface.

The restarter jet includes a restarter inlet and a slot. The restarter inlet is located in the flange outer surface and extends up to the flange contact surface. The slot extends from the restarter inlet through a portion of the flange along flange contact surface and through a portion of the body along the body outer surface up to a restarter outlet location proximal the body end surface. The slot is curved to redirect air entering the restarter jet at the restarter inlet in a first direction to exit the restarter jet at the restarter outlet location in a second direction.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic illustration of an exemplary gas turbine engine.

FIG. 2 is a cross-sectional view of a portion of the combustion chamber for the gas turbine engine of FIG. 1.

FIG. 3 is a perspective view of a first embodiment of the insert of FIG. 2.

FIG. 4 is a cross-sectional view of the insert of FIG. 3.

FIG. 5 is a cross-sectional view of the insert of FIG. 3 cutting through the insert at a different location.

FIG. 6 is a cross-sectional view of the insert of FIG. 3 joined to the combustion chamber.

FIG. 7 is a cross-sectional view of the insert of FIG. 3 joined to the combustion chamber cutting through the insert and the combustion chamber at a different location.

FIG. 8 is a perspective view of a second embodiment of the insert of FIG. 2.

FIG. 9 is a cross-sectional view of the insert of FIG. 8.

FIG. 10 is a cross-sectional view of the insert of FIG. 8 cutting through the insert at a different location.

FIG. 11 is a perspective view of a third embodiment of the insert of FIG. 2.

FIG. 12 is a cross-sectional view of the insert of FIG. 11.

FIG. 13 is a perspective view of a fourth embodiment of the insert of FIG. 2.

FIG. 14 is a cross-sectional view of the insert of FIG. 13.

FIG. 15 is a cross-sectional view of the insert of FIG. 8 joined to the combustion chamber.

FIG. 16 is a cross-sectional view of the insert of FIG. 8 joined to the combustion chamber cutting through the insert and the combustion chamber at a different location.

FIG. 17 is a cross-sectional view of the insert of FIG. 13 joined to the combustion chamber.

DETAILED DESCRIPTION

The systems and methods disclosed herein include a combustion chamber with inserts located in the combustion air holes that direct combustion air into the combustion chamber. The inserts include restarter jets configured to redirect air, such as combustion air, along an inner surface of the combustion chamber immediately downstream of the combustion air holes. Redirecting air immediately downstream of the combustion air holes may supplement or re-establish a cooling film, which may maintain a buffer between the liner wall of the combustion chamber and the high temperatures generated during the combustion process. Maintaining the cooling film may result in improved performance and durability of the combustion chamber.

FIG. 1 is a schematic illustration of an exemplary gas turbine engine 100. Some of the surfaces have been left out or exaggerated (here and in other figures) for clarity and ease of explanation. Also, the disclosure may reference a forward and an aft direction. Generally, all references to “forward” and “aft” are associated with the flow direction of primary air (i.e., air used in the combustion process), unless specified otherwise. For example, forward is “upstream” relative to primary air flow, and aft is “downstream” relative to primary air flow.

In addition, the disclosure may generally reference a center axis 95 of rotation of the gas turbine engine, which may be generally defined by the longitudinal axis of its shaft 120 (supported by a plurality of bearing assemblies 150). The center axis 95 may be common to or shared with various other engine concentric components. All references to radial, axial, and circumferential directions and measures refer to center axis 95, unless specified otherwise, and terms such as “inner” and “outer” generally indicate a lesser or greater radial distance from center axis 95, wherein a radial 96 may be in any direction perpendicular and radiating outward from center axis 95.

A gas turbine engine 100 includes an inlet 110, a shaft 120, a compressor 200, a combustor 300, a turbine 400, an exhaust 500, and a power output coupling 600. The gas turbine engine 100 may have a single shaft or a dual shaft configuration.

The compressor 200 includes a compressor rotor assembly 210, compressor stationary vanes (stators) 250, and inlet guide vanes 255. The compressor rotor assembly 210 mechanically couples to shaft 120. As illustrated, the compressor rotor assembly 210 is an axial flow rotor assembly. The compressor rotor assembly 210 includes one or more compressor disk assemblies 220. Each compressor disk assembly 220 includes a compressor rotor disk that is circumferentially populated with compressor rotor blades. Stators 250 axially follow each of the compressor disk assemblies 220. Each compressor disk assembly 220 paired with the adjacent stators 250 that follow the compressor disk assembly 220 is considered a compressor stage. Compressor 200 includes multiple compressor stages. Inlet guide vanes 255 axially precede the compressor stages.

The combustor 300 includes a combustion chamber 320 and one or more fuel injectors 310. Combustion chamber 320 includes combustion air holes 327 extending through the combustion walls of the outer liner 321 and the inner liner 331 with inserts 360 located in one or more of the combustion air holes 327 as described in further detail below (refer to FIG. 2). The fuel injectors 310 may be upstream of the combustion chamber 320 and may be annularly arranged about center axis 95.

The turbine 400 includes a turbine rotor assembly 410 and turbine nozzles 450. The turbine rotor assembly 410 mechanically couples to the shaft 120. In the embodiment illustrated, the turbine rotor assembly 410 is an axial flow rotor assembly. The turbine rotor assembly 410 includes one or more turbine disk assemblies 420. Each turbine disk assembly 420 includes a turbine disk that is circumferentially populated with turbine blades. Turbine nozzles 450 axially precede each of the turbine disk assemblies 420. Each turbine disk assembly 420 paired with the adjacent turbine nozzles 450 that precede the turbine disk assembly 420 is considered a turbine stage. Turbine 400 includes multiple turbine stages.

The exhaust 500 includes an exhaust diffuser 510 and an exhaust collector 520. The power output coupling 600 may be located at an end of shaft 120.

FIG. 2 is a cross-sectional view of a portion of the combustion chamber 320 for the gas turbine engine 100 of FIG. 1. FIG. 2 may not show portions of the combustion chamber 320 not present on the plane cutting through the combustion chamber 320 for clarity. Combustion chamber 320 may include a dome plate 350, heat shields 351, an outer liner 321, and an inner liner 331. Dome plate 350 may include an annular or toroidal shape that extends between outer liner 321 and inner liner 331. The axis of dome plate 350 may be concentric to center axis 95. Dome plate 350 may form the axial end of combustion chamber 320 where a fuel and air mixture is injected into the combustion chamber 320. Dome plate 350, outer liner 321, and inner liner 331 may define combustion zone 312.

Dome plate 350 includes one or more injector openings 352. Injector openings 352 may be circumferentially and evenly spaced about the axis of dome plate 350, and may be radially centered between outer liner 321 and inner liner 331 or located at the circumferential center of dome plate 350, concentric to an injector axis 395.

One or more heat shields 351 may be located axially aft of dome plate 350. Heat shields 351 may be bonded or otherwise connected to dome plate 350. Heat shields 351 may include an annular sector shape and may be circumferentially located to form an annulus.

Outer liner 321 includes an outer combustion wall 326. The outer combustion wall 326 may generally extend axially with a hollow cylinder shape that defines the outer boundary of combustion zone 312. The aft end of outer combustion wall 326 may have a hollow frustoconical shape with the narrower portion of the hollow frustum downstream of the wider portion so that the aft end narrows towards inner liner 331. Outer combustion wall 326 may be subdivided into multiple segments joined together. Some segments also include a louver 335 that overlaps with a downstream segment. In the embodiment illustrated, outer liner 321 includes a first outer liner segment 322, a second outer liner segment 323, and a third outer liner segment 324. First outer liner segment 322 is joined to second outer liner segment 323, and second outer liner segment 323 is joined to third outer liner segment 324. The outer liner segments may be joined by a metallurgical bond, such as a weld or braze.

Outer liner 321 may include an outer plenum wall 328. Outer plenum wall 328 is located radially outward from outer combustion wall 326 forming an outer plenum 329 there between. Outer plenum 329 may be a duct for combustor air, cooling air, and the like and may generally have an annular shape. Outer plenum wall 328 may generally have a hollow cylinder shape. Outer plenum wall 328 may also have an aft end with a hollow frustoconical shape with the narrower portion of the hollow frustum downstream of the wider portion so that the aft end narrows towards inner liner 331. Outer combustion wall 326 and outer plenum wall 328 may be metallurgically bonded, such as welded or brazed at their frustoconical shaped aft ends.

In some embodiments, such as the embodiment illustrated, outer liner 321 is configured to cool outer combustion wall 326 with impingement cooling. In these embodiments, a profusion of impingement holes 337 extend through outer plenum wall 328 and are configured to direct cooling air through outer plenum wall 328 towards outer combustion wall 326 so that the cooling air will impinge outer combustion wall 326. In other embodiments, outer liner 321 does not include an outer plenum wall 328; in these embodiments, the combustion air and cooling air are ducted by other means.

Outer liner 321 also includes combustion air holes 327 extending through outer combustion wall 326. As illustrated, outer liner 321 may include a profusion of combustion air holes 327 extending through the various segments of outer combustion wall 326. The profusion of combustion air holes 327 may include combustion air holes 327 with varying diameters. The diameter of each combustion air hole 327 may depend on its location in outer combustion wall 326. Combustion air holes 327 provide a path for combustor air to pass from the outer plenum 329 into the combustion zone 312.

Inner liner 331 includes an inner combustion wall 336. The inner combustion wall 336 may generally extend axially with a hollow cylinder shape that defines the inner boundary of combustion zone 312. The aft end of inner combustion wall 336 may have a hollow frustoconical shape with the narrower portion of the hollow frustum upstream of the wider portion so that the aft end widens towards outer liner 321. Inner combustion wall 336 may be subdivided into multiple segments joined together. Some segments also include a louver 335 that overlaps with a downstream segment. In the embodiment illustrated, inner liner 331 includes a first inner liner segment 332, a second inner liner segment 333, and a third inner liner segment 334. First inner liner segment 332 is joined to second inner liner segment 333, and second inner liner segment 333 is joined to third inner liner segment 334. The inner liner segments may be joined by a metallurgical bond, such as a weld or braze.

Inner liner 331 may include an inner plenum wall 338. Inner plenum wall 338 is located radially inward from inner combustion wall 336 forming an inner plenum 339 there between. Inner plenum 339 may be a duct for combustor air, cooling air, and the like and may generally have an annular shape. Inner plenum wall 338 may generally have a hollow cylinder shape. Inner plenum wall 338 may also have an aft end with a hollow frustoconical shape with the narrower portion of the hollow frustum upstream of the wider portion so that the aft end widens towards outer liner 321. Inner combustion wall 336 and inner plenum wall 338 may be metallurgically bonded, such as welded or brazed at their frustoconical shaped aft ends.

In some embodiments, such as the embodiment illustrated, inner liner 331 is configured to cool inner combustion wall 336 with impingement cooling. In these embodiments, a profusion of impingement holes 337 extend through inner plenum wall 338 and are configured to direct cooling air through inner plenum wall 338 towards inner combustion wall 336 so that the cooling air will impinge inner combustion wall 336. In other embodiments, inner liner 331 does not include an inner plenum wall 338; in these embodiments, the combustion air and cooling air are ducted by other means.

Inner liner 331 also includes combustion air holes 327 extending through inner combustion wall 336. As illustrated, inner liner 331 may include a profusion of combustion air holes 327 extending through the various segments of inner combustion wall 336. The profusion of combustion air holes 327 may include combustion air holes 327 with varying diameters. The diameter of each combustion air hole 327 may depend on its location in inner combustion wall 336. Combustion air holes 327 provide a path for combustor air to pass from the inner plenum 339 into the combustion zone 312.

Combustion chamber 320 includes one or more inserts 360. Each insert 360 is located at a combustion air hole 327 extending through the combustion air hole 327 and a combustion wall, such as outer combustion wall 326 or inner combustion wall 336. As illustrated in FIG. 2, inserts 360 may vary in length with some inserts 360 are configured to only extend through a combustion wall, while other inserts 360 are configured to extend through both a combustion wall and a plenum wall, such as outer plenum wall 328 or inner plenum wall 338.

In some embodiments, each combustion air hole 327 includes an insert 360. In other embodiments, such as the embodiment illustrated in FIG. 2, not all combustion air holes 327 include an insert 360. Combustion air holes 327 with smaller diameters may not require an insert 360.

FIG. 3 is a perspective view of a first embodiment of the insert 360 of FIG. 2. In the embodiment illustrated, insert 360 includes a body 362 and a flange 361. Body 362 and flange 361 may be concentric to an insert axis 359. Body 362 may generally have a hollow cylinder shape. Body 362 may include a body end surface 363 and a body outer surface 365. Body end surface 363 may be located at an axial end of body 362. Body outer surface 365 may be adjacent body end surface 363 and may be the radially outer surface of body 362. Body outer surface 365 may be a cylindrical surface, such as a right circular cylinder. Flange 361 may be located at an end of body 362 opposite and distal to body end surface 363. Flange 361 may generally extend radially outward from body 362 relative to insert axis 359. Flange 361 includes a flange contact surface 367 and a flange outer surface 369. Flange contact surface 367 is adjacent body outer surface 365. Flange contact surface 367 may have an annular shape and may be perpendicular to insert axis 359. Flange outer surface 369 may be the radially outer surface of flange 361. Flange outer surface 369 may be adjacent contact surface 367. Flange outer surface 369 may be a cylindrical surface, such as a right circular cylinder

Insert 360 may also include combustor jet surface 366 and an insert edge break 364. Combustor jet surface 366 may be the interior surface of insert 360 and may form the combustor jet that directs combustion air into the combustion zone 312. Insert edge break 364 may extend between body outer surface 365 and flange contact surface 367. Insert edge break 364 may be an edge break, such as a fillet or chamfer.

Insert 360 also includes one or more restarter jets 370. Restarter jets 370 are generally configured to re-establish a cooling film along an inner surface of the outer combustion wall 326 or the inner combustion wall 336 immediately aft of combustion air holes 327. Restarter jets 370 include a restarter inlet 371 and a restarter outlet 372. The location of restarter inlet 371 depends on the configuration of the restarter jet 370, while the restarter outlet 372 is located in body outer surface 365 proximal body end surface 363. Restarter outlets 372 may primarily be located along a downstream portion of body outer surface 365. However, in some embodiments, some restarter outlets 372 are located along the sides of body outer surface 365 directing air along the outer liner 321 or the inner liner 331 transverse to the combustion flow path through the combustion zone 312.

FIG. 3 illustrates an embodiment of insert 360 with three restarter jets 370 with two restarter jet 370 configurations. As illustrated, insert 360 includes two slot type restarter jets 370 and one bore type restarter jet 370 there between. Insert 360 may be configured with any number of restarter jets 370 and may include multiple configurations of restarter jets 370. Restarter jets 370 may be circumferentially offset about body 362.

The slot type restarter jets 370 include a restarter inlet 371 at an outer surface of insert 360. In the embodiment illustrated, the restarter inlet 371 for the slot type restarter jet 370 is located in flange outer surface 369 and extends along flange outer surface 369 up to flange contact surface 367 so as to be bound by flange 361 on all but one side, the one side being located at flange contact surface 367. As illustrated, restarter inlet 371 has a rectangular shape with an open edge at flange contact surface 367. In other embodiments, restarter inlet 371 has a ‘U’ shape with an open edge at flange contact surface 367.

Restarter inlet 371 may be configured to form a bell mouth inlet with a restarter inlet surface 373 at each edge of the inlet bound by flange 361 Each restarter inlet surface 373 may be an edge break, such as a round or a chamfer. The round may transition from a cylindrical surface to a radially extending surface within restarter jet 370 transitioning from a circumferential direction to a radial direction. The radius of the round may not be constant and may increase or decrease during the transition.

FIG. 4 is a cross-sectional view of the insert 360 of FIG. 3. The cross-section in FIG. 4 is cut at the slot type restarter jet 370. Referring to FIGS. 3 and 4, restarter jet 370 may include a slot 381 extending from restarter inlet 371 to the restarter outlet 372 location. Slot 381 may be an open and curved slot, for example in the form of a groove, extending through a portion of flange 361 and through a portion of body 362. Slot 381 may include a constant radius of curvature. Slot 381 may have a rectangular or ‘U’ shaped cross-section.

Restarter jet 370 may include a bonding relief surface 375. The bonding relief surface 375 may be an edge break, such as a round or a chamfer extending along each edge of slot 381 towards restarter outlet 372. In the embodiment illustrated in FIGS. 3 and 4, bonding relief surface 375 extends from restarter inlet 371 along flange contact surface 367, insert edge break 364 and up body outer surface 365 towards the restarter outlet 372 location. Bonding relief surface 375 may taper, reducing in width while extending from the restarter inlet 371 towards the restarter outlet 372 location and terminates prior to the restarter outlet 372 location.

As illustrated in FIG. 4, combustor jet surface 366 may include an inlet portion 368. The inlet portion 368 may be configured to transition from a radial surface to a circumferential or cylindrical surface to form a bell mouth inlet to the combustor jet. Inlet portion 368 may be a hyperbolic funnel or a segment of a pseudosphere. Flange 361 may adjoin inlet portion 368.

FIG. 5 is a cross-sectional view of the insert of FIG. 3 cutting through the insert 360 at a different location. The cross-section in FIG. 5 is cut through a bore type restarter jet 370. Referring to FIGS. 3 and 5, restarter inlet 371 may be located in combustor jet surface 366. In the embodiment illustrated in FIG. 5, restarter jet 370 extends through body 362 and is angled so that restarter inlet 371 is closer to flange 361 than restarter outlet 372. As illustrated, the bore type restarter jet 370 includes a cylindrical shape. Alternatively, restarter jet 370 may include a frustoconical shape and may be configured increase or decrease the velocity of the air drawn from the combustor jet formed by combustor jet surface 366.

FIG. 6 is a cross-sectional view of the insert 360 of FIG. 3 joined to the combustion chamber 320. Inserts 360 may be metallurgically bonded, such as welded or brazed to a liner wall 319. Liner wall 319 may be an outer combustion wall 326 or an inner combustion wall 336. Liner wall 319 may include a combustion surface 316 that is inside the combustion chamber facing the combustion zone 312, a plenum surface 315 that is opposite the combustion surface 316 outside the combustion chamber, and a combustion hole surfaces 314 extending there between and forming the combustion air holes 327. Combustion surface 316 and plenum surface 315 may each include a cylindrical shape, such as a right circular cylinder. Flange contact surface 367 may be bonded to plenum surface 315 and body outer surface 365 may be bonded to a combustion hole surface 314.

As illustrated in FIG. 6, restarter jet 370 may be configured so that plenum surface 315 forms a part or portion of restarter inlet 371 and forms a part or portion of restarter jet 370, and combustion hole surface 314 forms another part or portion of restarter jet 370 so as to enclose the slot shape of restarter jet 370 between restarter inlet 371 and restarter outlet 372. The bonding relief surface 375 at each edge of restarter jet 370 may be configured to end at combustion surface 316. The restarter outlet 372 may be located adjacent combustion surface 316.

Liner wall 319 may also include a liner edge break 317 between plenum surface 315 and combustion hole surface 314. Liner edge break 317 may be an edge break, such as a fillet or a chamfer. A portion of liner edge break 317 may be configured to form a portion of restarter jet 370 and may be configured to not reduce the cross-sectional area of restarter jet 370. Liner edge break 317 may also be configured to prevent interference between insert 360 at insert edge break 364 and liner wall 319.

As further illustrated in FIG. 6, air may enter at restarter inlet 371 in a first direction and travel along restarter jet flow path 15 and may be redirected to exit at restarter outlet 372 in a second direction opposite the first direction.

Body 362 may protrude into the combustion zone 312 beyond combustion surface 316. Body end surface 363 may be located in the combustion zone 312 and may be angled relative to combustion surface 316 and may be angled relative to a surface perpendicular to the insert axis 359 so that an upstream portion of body end surface 363 is closer to combustion surface 316 than a downstream portion of body end surface 363. Body end surface 363 may be configured so that body 362 includes sufficient material between body end surface 363 and restarter outlet 372 to direct the air out of restarter jet 370 and to a desired location.

FIG. 7 is a cross-sectional view of the insert 360 of FIG. 3 joined to the combustion chamber 320 cutting through the insert 360 and the combustion chamber 320 at a different location. As illustrated in FIG. 7 restarter jet 370 may be configured to redirect a portion of combustor air traveling through insert 360 along combustor jet flow path 16 through body 362 and along combustion surface 316.

FIG. 8 is a perspective view of a second embodiment of the insert 360 of FIG. 2. In the embodiment illustrated in FIG. 8, body 362 is elongated and is configured to extend through a liner wall 319 and a plenum wall 318, such as outer plenum wall 328 or inner plenum wall 338, offset from the liner wall 319 (illustrated in FIGS. 15-18). FIG. 8 illustrates an embodiment of insert 360 with three restarter jets 370 with two restarter jet 370 configurations. In the embodiment illustrated, insert 360 includes two slot type restarter jets 370 and one channel type restarter jet 370 there between. Restarter jets 370 may be circumferentially offset about body 362.

FIG. 9 is a cross-sectional view of the insert 360 of FIG. 8. The cross-section in FIG. 9 is cut at the slot type restarter jet 370. Referring to FIGS. 8 and 9, restarter jet 370 may be an open and curved slot extending along a portion of body 362 proximal body end surface 363. The restarter jet 370 may include a constant radius of curvature. The restarter jet 370 may have a rectangular or ‘U’ shaped cross-section. Restarter inlet 371 may be located axially closer to flange 361 than restarter outlet 372.

Restarter jet 370 may include a bonding relief surface 375. The bonding relief surface 375 may be an edge break, such as a round or a chamfer, extending along each edge of restarter jet 370 from restarter inlet 371 towards restarter outlet 372. In the embodiment illustrated in FIGS. 8 and 9, bonding relief surface 375 extends from restarter inlet 371 along each side of restarter jet 370 at body outer surface 365. Bonding relief surface 375 may taper so that the edge break gets smaller as it extends from the restarter inlet 371 so as to terminate prior to restarter outlet 372. A restarter inlet surface 373 may extend along the circumferential edge of restarter inlet 371 closest to flange 361. The portion of the bonding relief surface 375 at each side of restarter inlet 371 may be configured to form a bell mouth inlet with restarter inlet surface 373 at restarter inlet 371.

FIG. 10 is a cross-sectional view of the insert 360 of FIG. 8 cutting through the insert 360 at a different location. Referring to FIGS. 8 and 10, restarter jet 370 may include a channel 379 extending axially within body 362. As illustrated in FIG. 10, restarter jet 370 may have an annular shape. Restarter inlet 371 may be located in inlet portion 368. Alternatively, in embodiments where combustor jet surface 366 is a right circular cylinder extending to flange 361, restarter inlet 371 is located in a flange end surface 378 located opposite flange contact surface 367. Restarter outlet 372 may be a hole or a slot extending from body outer surface 365 to channel 379.

FIG. 11 is a perspective view of a third embodiment of the insert 360 of FIG. 2. FIG. 12 is a cross-sectional view of the insert 360 of FIG. 11. As illustrated in FIGS. 11 and 12, channel 379 and restarter outlet 372 may be circumferentially elongated. Alternatively, channel 379 may be circumferentially elongated and insert 360 may include multiple restarter outlets 372 extending from body outer surface 365 to channel 379.

FIG. 13 is a perspective view of a fourth embodiment of the insert 360 of FIG. 2. FIG. 14 is a cross-sectional view of the insert 360 of FIG. 13. Similar to the restarter inlet 371 of FIGS. 3 and 4, the embodiment illustrated in FIGS. 13 and 14 is located in flange outer surface 369 and may include the same features as described previously. Slot 381 may initially curve from a radial direction to an axial direction while extending from flange outer surface 369 into body 362. Slot 381 may then extend axially in body 362 towards body end surface 363 and then may curve out at the restarter outlet 372 location.

In the embodiment illustrated, slot 381 is an open slot, for example in the form of a groove, in body outer surface 365 and insert 360 includes a sleeve 380 extending circumferentially around body outer surface 365 and extending axially between flange contact surface 367 and the location of restarter outlet 372. Sleeve 380 may be joined to body 362 by a metallurgical bond, such as a weld or braze. Alternatively, sleeve 380 is integral to body 362 and restarter jet 370 extends through body 362 similar to channel 379.

FIG. 15 is a cross-sectional view of the insert 360 of FIG. 8 joined to the combustion chamber 320. As illustrated in FIG. 15, inserts 360 may be elongated axially and configured to extend through a liner wall 319, such as outer combustion wall 326 or inner combustion wall 336, and extend through a plenum wall 318, such as outer plenum wall 328 or inner plenum wall 338.

Liner wall 319 and plenum wall 318 form a plenum 311, such as outer plenum 329 or inner plenum 339, there between. Plenum wall 318 may include a plenum wall first surface 341 and a plenum wall second surface 342. The plenum wall first surface 341 is located on the exterior of plenum wall 318. Plenum wall second surface 342 is opposite plenum wall first surface 341 and faces plenum surface 315. Plenum wall second surface 342 and plenum surface 315 form the boundary of plenum 311.

Plenum wall 318 also includes a plenum wall combustion hole surface 313 extending between the plenum wall first surface 341 and the plenum wall second surface 342 and forming a plenum wall combustion hole 343. Plenum wall combustion hole surface 313 may be a cylindrical surface and may be axially aligned with a combustion hole surface 314.

Inserts 360 may be metallurgically bonded, such as welded or brazed to a liner wall 319 and to a plenum wall 318. Flange contact surface 367 may be bonded to plenum wall first surface 341. Body outer surface 365 may be bonded to a combustion hole surface 314 and to a plenum wall combustion hole surface 313.

As illustrated in FIG. 15, restarter jet 370 may be configured so that combustion hole surface 314 forms a portion of restarter jet 370 so as to enclose the slot shape of restarter jet 370 between restarter inlet 371 and restarter outlet 372. Body 362 is positioned through liner wall 319 so that restarter inlet 371 is adjacent plenum surface 315 and restarter outlet 372 is adjacent combustion surface 316. In the embodiment illustrated, air from plenum 311 is directed through restarter jet 370 and out of restarter outlet 372 along combustion surface 316.

Body 362 may protrude into the combustion zone 312 beyond combustion surface 316. Body end surface 363 may be located in the combustion zone 312 and may be angled relative to combustion surface 316 so that an upstream portion of body end surface 363 is closer to combustion surface 316 than a downstream portion of body end surface 363. Body end surface 363 may also be angled so that a first side of the body end surface 363 adjacent the restarter outlet location is further from the flange contact surface 367 than a second side of the body end surface 363 opposite the first side of the body end surface 363.

FIG. 16 is a cross-sectional view of the insert 360 of FIG. 8 joined to the combustion chamber 320 cutting through the insert 360 and the combustion chamber 320 at a different location. As illustrated in FIG. 16, air from the outside of plenum 311 may enter restarter inlet 371 at or adjacent to flange 361 and travel along a restarter jet flow path 15 axially through body 362 and be directed along combustion surface 316.

FIG. 17 is a cross-sectional view of the insert of FIG. 13 joined to the combustion chamber. Sleeve 380 is configured to extend at least between the plenum surface 315 and the plenum wall second surface 342. In the embodiment illustrated, sleeve 380 extends from flange contact surface 367 to restarter outlet 372 and is joined to combustion hole surface 314 and plenum wall combustion hole surface 313. In other embodiments, sleeve 380 extends from plenum surface 315 to plenum wall second surface 342 and body outer surface 365 is joined to combustion hole surface 314 and plenum wall combustion hole surface 313. Similar to other embodiments, flange contact surface 367 is joined to plenum wall first surface 341.

As illustrated, restarter jet 370 may be configured so that plenum wall first surface 341 forms a portion of restarter inlet 371 and forms a portion of restarter jet 370. The restarter outlet 372 may be located adjacent combustion surface 315. Air may enter at restarter inlet 371 in a first direction and travel along restarter jet flow path 15 and may be redirected to exit at restarter outlet 372 in a second direction opposite the first direction.

One or more of the above components (or their subcomponents) may be made from stainless steel and/or durable, high temperature materials known as “superalloys”. A superalloy, or high-performance alloy, is an alloy that exhibits excellent mechanical strength and creep resistance at high temperatures, good surface stability, and corrosion and oxidation resistance. Superalloys may include materials such as HASTELLOY, alloy x, INCONEL, WASPALOY, RENE alloys, HAYNES alloys, alloy 188, alloy 230, INCOLOY, MP98T, TMS alloys, and CMSX single crystal alloys.

INDUSTRIAL APPLICABILITY

Gas turbine engines may be suited for any number of industrial applications such as various aspects of the oil and gas industry (including transmission, gathering, storage, withdrawal, and lifting of oil and natural gas), the power generation industry, cogeneration, aerospace, and other transportation industries.

Referring to FIG. 1, a gas (typically air 10) enters the inlet 110 as a “working fluid”, and is compressed by the compressor 200. In the compressor 200, the working fluid is compressed in an annular flow path 115 by the series of compressor disk assemblies 220. In particular, the air 10 is compressed in numbered “stages”, the stages being associated with each compressor disk assembly 220. For example, “4th stage air” may be associated with the 4th compressor disk assembly 220 in the downstream or “aft” direction, going from the inlet 110 towards the exhaust 500). Likewise, each turbine disk assembly 420 may be associated with a numbered stage.

Once compressed air 10 leaves the compressor 200, it enters the combustor 300, where it is diffused and fuel is added. Air 10 and fuel are injected into the combustion chamber 320 and combusted. An air and fuel mixture is supplied via fuel injector 310, while air for combustion is also supplied via combustion air holes 327. Energy is extracted from the combustion reaction via the turbine 400 by each stage of the series of turbine disk assemblies 420. Exhaust gas 90 may then be diffused in exhaust diffuser 510, collected and redirected. Exhaust gas 90 exits the system via an exhaust collector 520 and may be further processed (e.g., to reduce harmful emissions, and/or to recover heat from the exhaust gas 90).

Operating efficiency of a gas turbine engine generally increases with a higher combustion temperature. Thus, there is a trend in gas turbine engines to increase the combustion temperatures, which may be 538 degrees Celsius (1000 degrees Fahrenheit) or more. To operate at such high temperatures a portion of the compressed air of the compressor 200 of the gas turbine engine 100 may be diverted through internal passages or chambers to cool, inter alia, outer liner 321 and inner liner 331. A film of cooling air may be directed along combustion surfaces 316 to insulate the liner walls 319 from the higher temperature of the combusted gases.

Combustor air entering the combustion chamber 320 through combustion air holes 327 may disrupt the film of cooling air, which may result in an absence of the film cooling air directly downstream of the combustion air holes 327. The absence of the cooling film may subject outer liner 321 and the inner liner 331 to high temperatures, which may adversely affect the performance and durability of the combustion chamber 320.

Inserts 360 located in the combustion air holes 327 and plenum wall combustion holes 343 include one or more restarter jets 370 that are configured to direct air from one or more locations, such as the outer plenum 329, the inner plenum 339, or other ducting within the gas turbine engine 100, to the combustion surface 316, which may reestablish the cooling film at or redirect the cooling film to the areas of the liner walls 319 downstream of the combustion air holes 327 and may improve the performance and durability of the combustion chamber 320.

As illustrated in FIGS. 8-10 and 15-16, some embodiments may include multiple restarter jets 370 drawing air from multiple locations that have varying temperatures and pressures. The number of restarter jets 370 and the location that each restarter jet 370 draws air from may be based on the conditions in a given location of the combustion chamber 320. Use of air at varying temperatures and pressures may also reduce losses and improve overall efficiency of the gas turbine engine 100.

Multiple configurations of inserts 360 including the length of body 362, the number of restarter jets 370, the placement of restarter jets 370, and the configuration of each restarter jet 370 may be used within a single combustion chamber 320. The requirements to reestablish the cooling film downstream of each combustion air hole 327 may vary depending on the location of the combustion air hole 327. Using multiple configurations of inserts 360 within a combustion chamber 320 may limit the amount of combustion air used to reestablish the cooling film and may improve the overall efficiency of the system.

The preceding detailed description is merely exemplary in nature and is not intended to limit the invention or the application and uses of the invention. The described embodiments are not limited to use in conjunction with a particular type of gas turbine engine or a particular combustion chamber. Hence, although the present disclosure, for convenience of explanation, depicts and describes a particular insert for a combustion chamber, it will be appreciated that the insert in accordance with this disclosure can be implemented in various other configurations, can be used with various other types of combustion chambers and gas turbine engines, and can be used in other types of machines. Furthermore, there is no intention to be bound by any theory presented in the preceding background or detailed description. It is also understood that the illustrations may include exaggerated dimensions to better illustrate the referenced items shown, and are not consider limiting unless expressly stated as such.

Claims

1. An insert for combustion air holes in a liner wall of a combustion chamber for a gas turbine engine, the insert comprising:

a body having a first cylindrical shape with an insert axis, the body including a body outer surface that is a first cylindrical surface forming an outer surface of the body, a combustor jet surface located radially inward from the body outer surface forming a jet for directing combustion air into the combustion chamber, and a body end surface located at an axial end of the body and adjacent to the body outer surface and the combustor jet surface;

a flange located at an opposite end of the body relative to the body end surface, the flange including a flange contact surface adjacent the body outer surface, the flange contact surface having an annular shape, and a flange outer surface adjacent the flange contact surface, the flange outer surface having a second cylindrical shape located radially outward from the body outer surface; and

a restarter jet including a restarter inlet located in the flange outer surface and extending up to the flange contact surface, and a slot extending from the restarter inlet through a first portion of the flange along the flange contact surface and through a second portion of the body along the body outer surface up to a restarter outlet location proximal the body end surface, the slot being curved to redirect air entering the restarter jet at the restarter inlet in a first direction to exit the restarter jet at the restarter outlet location in a second direction.

2. The insert of claim 1, wherein the restarter inlet includes a bell mouth surface adjacent the flange outer surface forming a transition from the flange outer surface to the slot.

3. The insert of claim 2, wherein the bell mouth surface is a round that transitions from a circumferential direction to a radial direction.

4. The insert of claim 1, wherein the restarter jet includes a bonding relief surface extending from the restarter inlet along the slot 381 towards the restarter outlet location, the bonding relief surface being an edge break.

5. The insert of claim 4, wherein the bonding relief surface tapers, reducing in width while extending from the restarter inlet towards the restarter outlet location and terminates prior to the restarter outlet location.

6. The insert of claim 1, wherein the body end surface is angled so that a first side of the body end surface adjacent the restarter outlet location is further from the flange contact surface than a second side of the body end surface opposite the first side of the body end surface.

7. The insert of claim 1, further comprising a second restarter jet extending through the body and being circumferentially offset from the restarter jet, the second restarter jet including a second restarter inlet located in the combustor jet surface and a second restarter outlet located in the body outer surface proximal to the body end surface, the second restarter jet being angled so that the second restarter inlet is axially closer to the flange than the second restarter outlet.

8. The insert of claim 1, further comprising a sleeve joined to the body outer surface, the sleeve extending circumferentially around the body outer surface and extending axially between the flange contact surface and the restarter outlet location.

9. A combustion chamber of a gas turbine engine, the combustion chamber comprising:

a liner wall including a combustion surface located inside of the combustion chamber, a plenum surface opposite the combustion surface and located outside the combustion chamber, and a combustion hole surface extending from the combustion surface to the plenum surface forming a combustion air hole through the liner wall, the combustion hole surface having a first cylindrical shape; and

an insert including a body extending through the combustion air hole and having an insert axis, the body including a body outer surface forming an outer surface of the body, the body outer surface having a second cylindrical shape and being located radially inward from the combustion hole surface relative to the insert axis, a combustor jet surface located radially inward from the body outer surface forming a jet for directing combustion air through the liner wall and into the combustion chamber, and a body end surface located at an axial end of the body, adjacent to the body outer surface and the combustor jet surface, and located inside the combustion chamber, a flange located at an opposite end of the body relative to the body end surface, outside of the combustion chamber, the flange including a flange contact surface having an annular shape adjacent the body outer surface, and a flange outer surface adjacent the flange contact surface, the flange outer surface having a third cylindrical shape located radially outward from the body outer surface, and

a restarter jet including a restarter inlet located in the flange, a restarter outlet located in the body outer surface proximal the body end surface and adjacent the combustion surface, and a slot extending from the restarter inlet through the flange along the flange contact surface and through the body along the body outer surface to the restarter outlet, wherein a portion of the slot is formed by the combustion hole surface.

10. The combustion chamber of claim 9, wherein the restarter inlet includes a bell mouth surface adjacent the flange outer surface forming a transition from the flange outer surface to the slot.

11. The combustion chamber of claim 10, wherein the bell mouth surface is a round that transitions from a circumferential direction to a radial direction.

12. The combustion chamber of claim 9, wherein the restarter inlet is located adjacent the plenum surface with the plenum surface forming a portion of the restarter inlet.

13. The combustion chamber of claim 12, wherein the restarter jet includes a bonding relief surface extending from the restarter inlet along the slot towards the restarter outlet adjacent the plenum surface and adjacent the combustion hole surface, the bonding relief surface being an edge break.

14. The combustion chamber of claim 13, wherein the bonding relief surface tapers, reducing in width while extending from the restarter inlet towards the restarter outlet and terminates at the combustion surface.

15. The combustion chamber of claim 9, further comprising:

a plenum wall spaced apart from the liner wall forming a plenum there between, the plenum wall including a plenum wall first surface, a plenum wall second surface opposite the plenum wall first surface and facing the plenum surface, and a plenum wall combustion hole surface extending from the plenum wall first surface to the plenum wall second surface, the plenum wall combustion hole surface having a fourth cylindrical shape axially aligned with the combustion hole surface;

wherein the body is elongated and extends through the plenum wall at the plenum wall combustion hole and the restarter inlet is located adjacent the plenum wall first surface with the plenum wall first surface forming a portion of the restarter inlet; and

wherein the insert includes a sleeve extending circumferentially around the body outer surface and extending axially at least between the plenum surface and the plenum wall second surface.

16. The combustion chamber of claim 15, further comprising a second restarter jet including a second restarter inlet located adjacent the plenum surface and a second restarter outlet located adjacent the combustion surface.

17. An insert for combustion air holes in a liner wall of a combustion chamber for a gas turbine engine, the insert comprising:

a body having a cylindrical shape with an insert axis, the body including a body outer surface that is a first cylindrical surface forming an outer surface of the body, a combustor jet surface located radially inward from the body outer surface forming a combustor jet for directing combustion air into the combustion chamber, the combustor jet surface including an inlet portion, the inlet portion forming a bell mouth inlet into the combustor jet, and a body end surface located at an axial end of the body adjacent to the body outer surface and the combustor jet surface;

a flange located at an opposite end of the body relative to the body end surface and adjoining the inlet portion; and

a restarter jet including a restarter inlet located in the inlet portion, a channel extending from the restarter inlet axially through the body towards the body end surface relative to the insert axis, and a restarter outlet extending from the body outer surface to the channel, the restarter outlet being located proximal the body end surface.

18. The insert of claim 17, wherein the restarter inlet includes a bell mouth surface adjacent the inlet portion forming a transition from the inlet portion to the channel.

19. The insert of claim 17, wherein the channel is an annular shape having a circumferential span with an angular distance up to 90 degrees within the body.

20. The insert of claim 17, wherein the body is elongated so as to extend through the liner wall and through a plenum wall, the plenum wall being offset from the liner wall.