GAS TURBINE ENGINE COMPONENTS WITH COOLING HOLE TRENCHES
An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface; and a nonconcave trench extending from the cooling hole to the exterior surface of the body in a downstream direction such that cooling air flow from within the body flow through the cooling hole, through the trench, and onto the exterior surface.
Latest HONEYWELL INTERNATIONAL INC. Patents:
- Automated vegetation management system
- Apparatus and method for removal of a target gas from a cold storage environment
- Apparatuses, computer-implemented methods, and computer program product to assist aerial vehicle pilot for vertical landing and/or takeoff
- Systems and methods for displaying facility information
- Method and system for calibrating a gas detector
The present invention generally relates to gas turbine engines, and more particularly relates to air cooled components of gas turbine engines, such as turbine and combustor components.
BACKGROUNDGas turbine engines are generally used in a wide range of applications, such as aircraft engines and auxiliary power units. In a gas turbine engine, air is compressed in a compressor, and mixed with fuel and ignited in a combustor to generate hot combustion gases, which flow downstream into a turbine section. In a typical configuration, the turbine section includes rows of airfoils, such as stator vanes and rotor blades, disposed in an alternating sequence along the axial length of a generally annular hot gas flow path. The rotor blades are mounted at the periphery of one or more rotor disks that are coupled in turn to a main engine shaft. Hot combustion gases are delivered from the engine combustor to the annular hot gas flow path, thus resulting in rotary driving of the rotor disks to provide an engine output.
Due to the high temperatures in many gas turbine engine applications, it is desirable to regulate the operating temperature of certain engine components, particularly those within the mainstream hot gas flow path, in order to prevent overheating and potential mechanical issues attributable thereto. As such, it is desirable to cool the rotor blades and stator vanes in order to prevent damage and extend useful life. One mechanism for cooling turbine airfoils is to duct cooling air through internal passages and then vent the cooling air through holes formed in the airfoil. The holes are typically formed uniformly along a line substantially parallel to the leading edge of the airfoil and at selected distances from the leading edge to provide a film of cooling air over the convex side of the airfoil when the cooling air flows through them during engine operation. Other rows of cooling holes or an array of holes may be formed in the airfoil components depending upon design constraints. Film cooling attempts to maintain the airfoils at temperatures that are suitable for their material and stress level.
A typical film cooling hole is a cylindrical aperture inclined relative to the surface of the airfoil. In many conventional engines, however relatively high disadvantageous cooling air flows have been used to obtain satisfactory temperature control of engine components.
Accordingly, it is desirable to provide a gas turbine engine with improved film cooling. In addition, it is desirable to provide air-cooled turbine components with improved hole configurations. Furthermore, other desirable features and characteristics of the present invention will become apparent from the subsequent detailed description of the invention and the appended claims, taken in conjunction with the accompanying drawings and this background of the invention.
BRIEF SUMMARYIn accordance with an exemplary embodiment, an engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface; and a nonconcave trench extending from the cooling hole to the exterior surface of the body in a downstream direction such that cooling air flow from within the body flow through the cooling hole, through the trench, and onto the exterior surface.
In accordance with another exemplary embodiment, a turbine section of a gas turbine engine includes a housing defining a hot gas flow path; a plurality of circumferential rows of airfoils disposed in the hot gas flow path; a plurality of cooling holes arranged within at least one of the plurality of circumferential rows of airfoils; and a plurality of trenches, each of the plurality of trenches being associated with one of the plurality of cooling holes. Each of the trenches is defined by a straight bottom wall extending downstream of the respective cooling hole to an exterior surface of the respective airfoil.
In accordance with yet another exemplary embodiment, a turbine section of a gas turbine engine includes a housing defining a hot gas flow path; a plurality of circumferential rows of airfoils disposed in the hot gas flow path; a plurality of cooling holes arranged within at least one of the plurality of circumferential rows of airfoils; and a plurality of trenches, each of the plurality of trenches being associated with one of the plurality of cooling holes. Each of the trenches is defined by a convex bottom wall extending downstream of the respective cooling hole to an exterior surface of the respective airfoil.
The present invention will hereinafter be described in conjunction with the following drawing figures, wherein like numerals denote like elements, and wherein:
The following detailed description is merely exemplary in nature and is not intended to limit the invention or the application and uses of the invention. Furthermore, there is no intention to be bound by any theory presented in the preceding background or the following detailed description.
Broadly, exemplary embodiments discussed herein include gas turbine engines with turbine components having improved film cooling. The turbine components have a number of circular or non-circular cooling holes. Additionally, the cooling holes have a nonconcave trench at the surface of the turbine component that extends in a downstream direction to improve film cooling.
The stator vanes 122 project radially outwardly from a circumferential platform 126 to the annular duct wall 104. The rotor blades 124 project radially outwardly from a circumferential platform 128 that is adapted for appropriate connection to the rotor disk (not shown) at the periphery thereof. The rotor disk is generally positioned within the internal engine cavity and is coupled to a main engine shaft for rotation therewith. As shown, the rotor blade 124 and stator vane 122 may form one stage of a multistage turbine. As such, multiple rows of the stator vanes 122 and the rotor blades 124 may be provided in the turbine section 100, with the rotor blades 124 and associated rotor disks being rotatably driven by the hot gas flow 108 for power extraction. A supply of cooling air, typically obtained as a bleed flow from the compressor (not shown), may pass through cooling holes in the stator vane 122 and rotor blade 124 to form a surface cooling film. Although the cooling holes are discussed with reference to turbine components, the cooling holes may also be incorporated into other engine components, such as combustor components. The cooling holes are discussed in greater detail below.
The airfoil 200 generally has a body 201 with a leading edge 202 and an opposite trailing edge 204. The airfoil 200 also includes a pressure sidewall 206 that is generally concave and an opposite, suction sidewall 208 that is generally convex and is spaced-apart from the pressure sidewall 206. The pressure sidewall 206 and suction sidewall 208 extend from leading edge 202 to trailing edge 204. The airfoil 200 has a hollow interior cavity 210 such that the airfoil 200 has an inner surface 212 and an outer surface 214. Airfoils 200 used in high performance gas turbine engines, such as those used for aircraft propulsion, can be made from high heat and high stress resistant aerospace alloys, such as nickel based alloys, Rene 88, Inconel 718, single crystal materials, steels, titanium alloys or the like.
As noted above, the airfoil 200 is subject to high temperatures because high velocity hot gases are ducted from the combustor (not shown) onto the airfoil 200. If unaddressed, the extreme heat may affect the useful life of an airfoil. As such, film cooling is provided for the airfoil 200 to provide a cooling film of fluid onto the surface of the airfoil 200, particularly in the area of the leading edge 202 and areas immediately aft of the leading edge 202. As noted above, cooling air is bled from the compressor (not shown) or other source and passes into the interior cavity 210 and through cooling holes 220 to the outer surface 214 of the airfoil 200. The cooling holes 220 are formed at locations on the airfoil 200, particularly the pressure sidewall 206, suction sidewall 208, and leading edge 202, to provide optimum cooling of the engine component.
The cooling holes 220 may be formed in a selected pattern or array to provide optimum cooling. The cooling holes 220 may be disposed at any angle relative to the outer surface, such as about 20° to about 40°, although the cooling holes 220 may be oriented at lesser or greater angles. Computational fluid dynamics (CFD) analysis can additionally be used to optimize the location and orientation of the cooling holes 220. The cooling holes 220 may be formed by casting, abrasive water jet, Electron Discharge Machining (EDM), laser drilling, or any suitable process.
In general, the cooling holes 220 may be considered to have an upstream portion 222 adjacent the inner surface 212 and a downstream portion 224 adjacent the outer surface 214. The upstream portion of each cooling hole 220, lying closer to the inner surface 212, is substantially cylindrical or circular, and the downstream portion lying closer to the outer surface 214 may have a cross-sectional shape as discussed below with reference to
As noted above and best shown in
The downstream portion 312 of each cooling hole 220 is at least partially defined by or otherwise fluidly coupled to a trench 350. In general, the trench 350 provides improved film cooling at the surface 214 of the airfoil 200. The trench 350 enables the cooling air to remain attached to the surface 214 for a longer period of time and minimizes mixing of the cooling air and mainstream gas flow, thereby resulting in a more effective film. Relative to conventional arrangements, the trench 350 reduces the radial velocity (i.e., perpendicular to the surface 214) of the cooling air as it exits the cooling hole 220 to prevent surface separation. Typically, each cooling hole 220 is associated with a single trench 350, e.g., each trench 350 is only in fluid communication with a single hole and not other cooling holes or trenches. In general, and as discussed below, the trench 350 is arranged at the exit of the cooling hole 220 and is typically very close to the outer surface 214 of the airfoil 200.
In this embodiment, the trench 350 is defined in the outer surface 214 by a convex bottom wall 352 and extends in a downstream direction relative to the main gas flow to a length 354. In one exemplary embodiment, the bottom wall 352 is continuously convex for the length of the trench 350 (e.g., from the termination of the hole 220 to the exterior surface). The length 354 may be a function of a diameter 330 of the cooling hole 220. For example, the length 354 may be at least four times greater than the length 330. The length 354, may be, for example, six times the diameter (length 330 or width 340) of the hole; but it could be smaller or larger depending on the pitch of the holes.
In one exemplary embodiment, the radius of curvature of the trench bottom wall 352 may have approximately the same radius of curvature of the outer surface 316 of the section 300 of airfoil 200. In other words, the bottom wall 352 may have a shape that corresponds to the shape of the outer surface 316 rotated about an end point of the trench 350 (e.g., point 355 in
The trench 350 may have a first depth 360 at an upstream end that corresponds to the maximum depth of the trench 350, although in other embodiments, the maximum depth may be further downstream. In one exemplary embodiment, the first depth 360 is measured from beginning of the trench 350 normal to the surface of the outer surface 316. In some exemplary embodiments, the depth 360 may be a function of a diameter 330 of the cooling hole 220. As an example, the depth 360 may be approximately equal to the diameter 330 or less than, or approximately equal to, the diameter 330. As such, the length 354 of the trench 350 may be at least four times greater than the depth 360 of the trench 350 at the exit of hole 220. In other embodiments, the length 354 of the trench 350 may be at least seven to nine times greater than the depth 360. In one exemplary embodiment, the trench 350 may extend to a length 354 and lateral width 358 (
In general, the convex bottom wall 352 of the trench 350 may provide enhanced film fooling for a given air flow. For example, the convex bottom wall 352 may provide a smoother transition on the outer surface 214 of the airfoil 200 while reducing the radial velocity of the air flow. This results in the cooling flow maintaining attachment to the bottom wall 352 of the trench 350, and subsequently, the outer surface 214 in both the streamwise and lateral directions, e.g., by not separating and creating recirculation vortices that draw heated air onto the surface. Although the trench 350 in
As most clearly shown in
As most clearly shown in the top view of
Although not shown, the interior portion 302 may have other cross-sectional shapes in positions further upstream to the view of
As noted above, other nonconcave trench arrangements may be provided.
As best shown in
The downstream portion 724 of each cooling hole 720 is at least partially defined by a trench 750. In general, the trench 750 provides improved film cooling at the surface 714 of the airfoil 700. The trench 750 enables the cooling air to remain attached to the surface 714 for a longer period of time and minimizes mixing of the cooling air and mainstream gas flow, thereby resulting in a more uniform film. Relative to conventional arrangements, the trench 750 reduces the radial velocity (i.e., perpendicular to the surface 714) of the cooling air as it exits the cooling hole 720 to prevent surface separation.
The trench 750 is defined in the outer surface 714 by a straight or flat bottom wall 752 and extends in a downstream direction relative to the main gas flow to a length 754. In one exemplary embodiment, the bottom wall 752 is continuously straight for the length of the trench 750 (e.g., from the termination of the hole 720 to the exterior surface). The length 754 may be a function of a diameter of the cooling hole 720. For example, the length 754 may be at least four times greater than the length. The length 754 may be, for example, six times the diameter (length or width) of the hole; but it could be smaller or larger depending on the pitch of the holes.
The trench 750 may have a first depth at an upstream end that corresponds to the maximum depth of the trench 750, although in other embodiments, the maximum depth may be further downstream. In some exemplary embodiments, the depth may be a function of a diameter of the cooling hole 720. As an example, the depth may be approximately equal to the diameter. In other embodiments, the depth may be based on other criteria.
As noted above, the downstream portion 724 of each cooling hole 720 is substantially oval. The downstream portion 724 has a cross-sectional diameter (or length) along the major axis of the oval shape that is generally parallel to the mainstream gas flow and a cross-sectional diameter (or width) along the minor axis of the oval shape. In other embodiments, the cooling hole 720 may be circular or elliptical, e.g., such as the shapes discussed below.
In one exemplary embodiment, the angle 716 between the longitudinal axis or side wall of the downstream portion 724 of the cooling hole 720 and the bottom wall 752 of the trench 750 may be, for example, about 25-45°, e.g., 35°. However, the angle 716 may be any suitable angle.
In general, the cross-sectional shapes and trenches of the holes 220, 720, 600, 800, 900, 1000, 1100 facilitate the distribution of the cooling air substantially completely over the outer surface of the airfoil. In particular, the cross-sectional shapes and trenches function as a diffuser to reduce the velocity and increase static pressure of the cooling airstreams exiting the holes and encourage cooling film development. The trenches additionally increase the lateral spread distribution of the exiting airflows, decrease peak velocities, and improve adiabatic effectiveness across a number of blowing ratios. These airstreams are more inclined to cling to the surface for improved cooling rather than separate from the surface. This produces an enhanced cooling effect at the surface. In one exemplary embodiment, the airfoils with straight trench bottom walls (e.g., trench 750 of
Exemplary embodiments disclosed herein are generally applicable to air-cooled components, and particularly those that are to be protected from a thermally and chemically hostile environment. Notable examples of such components include the high and low pressure turbine nozzles and blades, shrouds, combustor liners and augmentor hardware of gas turbine engines. Additionally, the cooling holes discussed above may be incorporated into turbine components. The advantages are particularly applicable to gas turbine engine components that employ internal cooling to maintain the service temperature of the component at an acceptable level while operating in a thermally hostile environment. In other embodiments, the exemplary embodiments, including the trenches discussed above, may be incorporated into cooling holes of combustor components, including combustor liners.
While at least one exemplary embodiment has been presented in the foregoing detailed description of the invention, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the invention in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing an exemplary embodiment of the invention. It being understood that various changes may be made in the function and arrangement of elements described in an exemplary embodiment without departing from the scope of the invention as set forth in the appended claims.
Claims
1. An engine component, comprising:
- a body having an interior surface and an exterior surface;
- a cooling hole formed in the body and extending from the interior surface; and
- a nonconcave trench extending from the cooling hole to the exterior surface of the body in a downstream direction such that cooling air flow from within the body flow through the cooling hole, through the trench, and onto the exterior surface.
2. The engine component of claim 1, wherein the nonconcave trench is defined by a nonconcave bottom wall extending in the downstream direction.
3. The engine component of claim 1, wherein the nonconcave trench is defined by a straight bottom wall extending in the downstream direction.
4. The engine component of claim 3, wherein the straight bottom wall is continuously straight from the cooling hole to the exterior surface.
5. The engine component of claim 1, wherein the nonconcave trench is defined by a convex bottom wall extending in the downstream direction.
6. The engine component of claim 5, wherein the convex bottom wall is continuously convex from the cooling hole to the exterior surface.
7. The engine component of claim 1, wherein the cooling hole is a first cooling hole and the trench is a first cooling trench, and wherein the engine component further comprises additional cooling holes and additional trenches, each of the trenches being associated with a single cooling hole.
8. The engine component of claim 1, wherein the cooling hole has a first cross-sectional shape in downstream portion with a first leading edge having a first shape, and the nonconcave trench has a second leading edge having a second shape, the second shape being similar to the first shape.
9. The engine component of claim 1, wherein the cooling hole has a first length and the nonconcave trench extends in the downstream direction at a second length, the second length being at least three times the first length.
10. The engine component of claim 1, wherein the nonconcave trench has a first width at a first position and a second width at a second position that is downstream of the first position, the second width being greater than the first width.
11. The engine component of claim 1, wherein the cooling hole has a cross-sectional shape that is bean-shaped.
12. The engine component of claim 1, wherein the cooling hole has a cross-sectional shape that is triad-shaped.
13. The engine component of claim 1, wherein the cooling hole has a cross-sectional shape that is reverse B-shaped.
14. The engine component of claim 1, wherein the cooling hole has a cross-sectional shape that is dumbbell-shaped.
15. The engine component of claim 1, wherein the cooling hole has a cross-sectional shape that is a triangular.
16. The engine component of claim 1, wherein the cooling hole has a cross-sectional shape that is an oval.
17. A turbine section of a gas turbine engine, comprising:
- a housing defining a hot gas flow path;
- a plurality of circumferential rows of airfoils disposed in the hot gas flow path;
- a plurality of cooling holes arranged within at least one of the plurality of circumferential rows of airfoils; and
- a plurality of trenches, each of the plurality of trenches being associated with one of the plurality of cooling holes, wherein each of the trenches is defined by a straight bottom wall extending downstream of the respective cooling hole to an exterior surface of the respective airfoil.
18. The turbine section of claim 17, wherein each of the cooling holes has a cross-sectional area that is bean-shaped, triad-shaped, reverse-B shaped, or dumbbell-shaped.
19. A turbine section of a gas turbine engine, comprising:
- a housing defining a hot gas flow path;
- a plurality of circumferential rows of airfoils disposed in the hot gas flow path;
- a plurality of cooling holes arranged within at least one of the plurality of circumferential rows of airfoils; and
- a plurality of trenches, each of the plurality of trenches being associated with one of the plurality of cooling holes, wherein each of the trenches is defined by a convex bottom wall extending downstream of the respective cooling hole to an exterior surface of the respective airfoil.
20. The turbine section of claim 19, wherein each of the cooling holes has a cross-sectional area that is bean-shaped, triad-shaped, reverse-B shaped, or dumbbell-shaped.
Type: Application
Filed: May 22, 2012
Publication Date: Nov 28, 2013
Applicant: HONEYWELL INTERNATIONAL INC. (Morristown, NJ)
Inventors: Vighneswara Rao Kollati (Andhra Pradesh), Balamurugan Srinivasan (Bangalore), Jyothishkumar Venkataramanan (Tamil Nadu), Sujatha Guntu (Andhra Pradesh), Jong Liu (Scottsdale, AZ), Daniel Cregg Crites (Mesa, AZ), Luis Tapia (Maricopa, AZ), Malak Fouad Malak (Tempe, AZ)
Application Number: 13/477,883
International Classification: F04D 31/00 (20060101);