Abstract: A transition duct having a thermally free aft frame and being capable of adjusting the natural frequency is disclosed. The aft frame is capable of permitting movement due to thermal gradients with the transition duct. The transition duct utilizes a spring plate located adjacent to an aft mounting bracket, where the spring plate, based on its thickness can either increase or decrease a frequency of the transition duct. Such an arrangement ensures that the transition duct natural frequency does not coincide with or cross other critical engine and/or combustor frequencies.

Abstract: A transition duct assembly with a thermally free aft frame and mounting system for use in a gas turbine engine are disclosed. The aft frame is capable of adjusting to thermal gradients while the mounting system provides for at least transverse movement of the transition duct during engine assembly. The mounting system also provides a means for raising the natural frequency of the transition duct outside of the engine's dynamic excitation ranges.

Abstract: Embodiments for an apparatus and associated method for providing a cooling fluid to a gas turbine transition duct in order to lower the effective operating temperatures of the transition duct are disclosed. The transition duct has an inner liner and an impingement sleeve positioned radially outward with a passageway formed therebetween. The impingement sleeve has a plurality of openings where a portion of the openings each have a feed tube extending through the opening and into the passageway. The feed tubes are oriented at an angle relative to the impingement sleeve, such that an inlet to the feed tube is directed generally towards an oncoming flow of cooling fluid. The feed tubes direct a portion of the cooling fluid toward the inner liner and into the passageway for cooling of the transition duct.

Abstract: A sealing device for use between a gas turbine combustor transition duct aft frame and a turbine inlet having improved durability, reduced wear on the mating turbine vane, and reduced manufacturing costs, is disclosed. The sealing device has a circumferential length, an axial width, and a radial height and contains a plurality of channels extending axially along the seal inner surface for passing a controlled amount of cooling air to a turbine inlet. The sealing device is formed of abradable honeycomb having a plurality of honeycomb cells with the honeycomb cells oriented to ensure maximum control against cooling air leakage while also providing maximum flexibility during assembly. The sealing device is captured between the transition duct aft frame, bulkhead, and turbine vane platform, thereby allowing easy replacement of the seal without requiring major disassembly of the transition duct aft frame section.

Abstract: An improved sealing device for use between a transition duct aft frame and turbine inlet is disclosed. The improved sealing device includes a plurality of corrugated metal seals that are secured to the transition duct aft frame along the are-like sections of the aft frame. The corrugated seals contact both the transition duct aft frame and turbine inlet to provide a more effective seal and to control the amount of compressor discharge air introduced to cool the turbine vane platforms. In the preferred embodiment, the corrugated seals are coated to reduce wear, fretting, and galling and are used in conjunction with a transition duct thermally free aft frame and pivot bearing mounting system. An alternate embodiment of the seal is also disclosed that utilizes an alternate cooling hole pattern for providing additional cooling air to the turbine vane platform.

Abstract: An improved sealing device for use between a transition duct aft frame and turbine inlet is disclosed. The improved sealing device includes a plurality of corrugated metal seals that are secured to the transition duct aft frame along the arc-like sections of the aft frame. The corrugated seals contact both the transition duct aft frame and turbine inlet to provide a more effective seal and to control the amount of compressor discharge air introduced to cool the turbine vane platforms. In the preferred embodiment, the corrugated seals are coated to reduce wear, fretting, and galling and are used in conjunction with a transition duct thermally free aft frame and pivot bearing mounting system. An alternate embodiment of the seal is also disclosed that utilizes an alternate cooling hole pattern for providing additional cooling air to the turbine vane platform.

Abstract: A mounting system for fixturing a transition duct to a turbine inlet is disclosed. The mounting system includes a plurality of mounting plates having through holes and each plate having a spherical bearing, a plurality of washers, lock tabs, and a means for securing the mounting plates to the turbine inlet. In the preferred embodiment, the mounting system of the present invention is utilized to secure a transition duct having a thermally free aft frame to a turbine inlet.

Abstract: A transition duct having a panel assembly with an inlet end of generally circular cross section and an outlet end having a generally rectangular arc-like cross section is disclosed. The panel assembly has an uncoated internal profile substantially in accordance with coordinate values X, Y, and Z as set forth in Table 1 carried only to three decimal places wherein the coordinates are taken at a sweep angle &thgr; wherein &thgr; is an angle measured from said inlet end and X, Y, and Z are coordinates defining the panel assembly profile at each angle &thgr; from the inlet end. An alternate embodiment is also disclosed defining an envelope for the uncoated internal profile of the panel assembly.

Abstract: A transition duct with a thermally free aft frame for use in a gas turbine engine is disclosed. The transition duct includes an aft frame that is thermally free through the use of a plurality of retention lugs, bushings, and bulkhead assemblies. The aft frame is allowed to adjust from thermal changes as a result of relative sizing between the bushings and retention lugs of the aft frame. An additional feature of this invention is the use of radially extending ribs along the sidewalls of the aft frame, to form an interlocking sealing means with adjacent transition ducts to reduce the amount compressor air leakage into the turbine inlet.

Abstract: An effusion cooled transition duct for transferring hot gases from a combustor to a turbine is disclosed. The transition duct includes a panel assembly with a generally cylindrical inlet end and a generally rectangular exit end with an increased first and second radius of curvature, a generally cylindrical inlet sleeve, and a generally rectangular end frame. Cooling of the transition duct is accomplished by a plurality of holes angled towards the end frame of the transition duct and drilled at an acute angle relative to the outer wall of the transition duct. Effusion cooling geometry, including coverage area, hole size, and surface angle will be optimized in the transition duct to tailor the temperature levels and gradients in order to minimize thermally induced stresses. The combination of the increase in radii of curvature of the panel assembly with the effusion cooling holes reduces component stresses and increases component life.

Abstract: An effusion cooled transition duct for transferring hot gases from a combustor to a turbine is disclosed. The transition duct includes a panel assembly with a generally cylindrical inlet end and a generally rectangular exit end with an increased first and second radius of curvature, a generally cylindrical inlet sleeve, and a generally rectangular end frame. Cooling of the transition duct is accomplished by a plurality of holes angled towards the end frame of the transition duct and drilled at an acute angle relative to the outer wall of the transition duct. Effusion cooling geometry, including coverage area, hole size, and surface angle will be optimized in the transition duct to tailor the temperature levels and gradients in order to minimize thermally induced stresses. The combination of the increase in radii of curvature of the panel assembly with the effusion cooling holes reduces component stresses and increases component life.

Abstract: A retention clip cooperates with a bolt and a flange through which the bolt passes to retain the bolt during blind assembly. Opening 28 in flange 26 receives bolt 24. Retention clip 40 is retained with extension 50 in recess 34 by engagement of the clip with the bolt. The clip in turn retains bolt 24 by engaging head 22 with arms 52. Surface 32 is adjacent to flat 60 resisting rotation of the bolt.

Abstract: Blade platforms (26) for compressor blades with airfoils (22) in high solidity relationship have edges of a major portion (44) a minor portion (46), and a canted intermediate portion (48). Minimum clearance (54) exists between the major portions (44) whereby twisting during stackup or operation is avoided. A circumferential seal (60, 64) is located under the platform coincident with major portion (44).