Abstract: A swirler is provided for mixing air from a compressor and fuel from a fuel injector for discharge into a dome of a gas turbine engine combustor. The swirler includes a tubular ferrule for coaxially receiving the fuel injector. A plurality of circumferentially spaced apart swirl vanes are fixedly joined coaxially with the ferrule. An outlet tube is fixedly joined coaxially with the swirl vanes in flow communication therewith for receiving air from the swirlers and fuel from the fuel injector. An annular collar is fixedly joined around the outlet tube and has a convex spherical outer surface. An annular mounting flange for mounting the swirler to the combustor dome has a concave spherical inner surface disposed coaxially around the collar outer surface in a sliding fit therewith to define a ball joint for allowing relative rotation therebetween for self-aligning the fuel injector with the swirler.

Abstract: A gas turbine engine fuel injection assembly includes a combustor case surrounding a combustor having a dome. An arcuate manifold is disposed inside the combustor case adjacent to the dome, and includes a plurality of fuel injectors disposed in flow communication therewith for receiving fuel for injection into the combustor. An inlet stem is joined in flow communication with the manifold for channeling fuel thereto, and includes an inner fitting disposed in a mounting port in the combustor case. A mounting adaptor is joined to the combustor case at the mounting port, and circumferentially engages the inner fitting to restrain torsional movement thereof. An outer fitting extends in the adaptor and engages the inner fitting in flow communication therewith for supplying fuel thereto.

Abstract: An apparatus and method for effecting the disassembly of an annular combustor for the maintenance of very large power generation gas generators such as those used in military aircraft engines, commercial aircraft engines, and smaller power generation turbines. The apparatus utilizes rollers which are attachable to a lower half outer casing. An inversion ring located radially inward from the lower half outer casing is supported by the rollers. By disconnecting a removable upper half outer casing, the combustor segments of a first section of the combustor can be removed. Supports connected to the first section of the combustor are secured by pins to a tool ring which is in turn secured to the inversion ring so as to create a closed path. By removing pins which secure the inversion ring and lower half outer casing to supports connected to a second section of combustor segments, the combustor can be rotated so that the second section of formerly inaccessible segments can be easily removed.

Abstract: An air transfer assembly for a gas turbine engine is provided. The assembly transfers temperature control air from an annular plenum to an annular manifold through an air transfer tube interposed therebetween. The air transfer tube prevents temperature control air leakage even though it is permitted to slide between limits set by an air transfer bushing assembly and a manifold cup formed in the annular manifold. The air transfer bushing is removable and is installed in an aperature in an outer support. The manifold cup is formed in the annular manifold.

Abstract: The invention comprises a borescope plug for sealing a borescope inspection port on a turbine engine having a fluid flowpath and multiple casings. The borescope plug comprises a plug body having an interlocking drive interface, a plunger portion positioned for sliding coaxial movement relative to the plug body and spring means engaging both the plug body and the plunger. The spring means presses the plunger towards a fully extended position relative to the plug body. The plunger comprises a fixedly attached tip portion shaped to conform with the fluid flowpath. Key means is provided for aligning the tip to conform with the fluid flowpath and the tip is cooled with a cooling airflow.

Abstract: The invention comprises a boltless turbine nozzle and nozzle support assembly that includes a turbine nozzle mounting flange seated in a nozzle seat forming a part of the nozzle support. Pins are used for affixing the nozzle mounting flange to the nozzle support seat and baffles are provided for maintaining the pins in their desired locations. A retaining ring is preferrably used to retain the baffles adjacent to the pins. A pressure actuated pliable seal is affixed to the turbine nozzle adjacent to the nozzle seat in order to provide an air seal across the completed assembly.