Abstract: A diffuser system for a compressor for a gas turbine engine, the compressor having an impeller and the gas turbine engine having a combustor and a fuel injector proximate to the combustor, includes a first diffuser and a second diffuser. The first diffuser is configured to receive compressed air from the impeller. The second diffuser is coupled to receive the compressed air from the first diffuser. The second diffuser comprises a housing comprising a first wall and a second wall. The first and second walls form a diffuser flow passage therebetween. The first wall or the second wall, or both, further form an opening through the first and second walls for the fuel injector to pass through when removed from the combustor.

Abstract: A compressor includes a housing, a rotor, an impeller, and a ported shroud. The rotor is mounted within the housing, and has a first leading edge and a first trailing edge. The rotor is operable, upon rotation thereof, to compress air and to discharge the air in an approximately axial direction. The impeller is mounted within the housing, and has a second leading edge and a second trailing edge. The impeller is operable, upon rotation thereof, to receive the air discharged from the rotor, to further compress the air, and to discharge the air in an approximately radial direction. The shroud at least partially surrounds the impeller. The shroud has an opening therein to at least facilitate allowing the air to travel upstream of the opening.

Abstract: A compressor includes a diffuser, a recirculation duct, and a flow control valve. The recirculation duct has an inlet in fluid communication with the air outlet of the diffuser, and an outlet in fluid communication with the air inlet of the diffuser. The flow control valve is selectively moveable between open and closed positions, to thereby fluidly couple and isolate, respectively, the recirculation duct inlet and outlets. During operation of the compressor, the flow control valve may be opened, which circulates a portion of the compressed air discharged from the diffuser air outlet back to the diffuser air inlet. The air that is circulated back to the diffuser air inlet reduces the effective area of the diffuser air inlet, thereby increasing the surge margin of the compressor.

Abstract: A compressor includes a housing, a rotor, an impeller, and a ported shroud. The rotor is mounted within the housing, and has a first leading edge and a first trailing edge. The rotor is operable, upon rotation thereof, to compress air and to discharge the air in an approximately axial direction. The impeller is mounted within the housing, and has a second leading edge and a second trailing edge. The impeller is operable, upon rotation thereof, to receive the air discharged from the rotor, to further compress the air, and to discharge the air in an approximately radial direction. The shroud at least partially surrounds the impeller. The shroud has an opening therein to at least facilitate allowing the air to travel upstream of the opening.

Abstract: A diffuser system for a compressor for a gas turbine engine, the compressor having an impeller and the gas turbine engine having a combustor and a fuel injector proximate to the combustor, includes a first diffuser and a second diffuser. The first diffuser is configured to receive compressed air from the impeller. The second diffuser is coupled to receive the compressed air from the first diffuser. The second diffuser comprises a housing comprising a first wall and a second wall. The first and second walls form a diffuser flow passage therebetween. The first wall or the second wall, or both, further form an opening through the first and second walls for the fuel injector to pass through when removed from the combustor.

Abstract: A nonlinearly stacked low noise turbofan stator vane having a characteristic curve that is characterized by a nonlinear sweep and a nonlinear lean is provided. The stator is in an axial fan or compressor turbomachinery stage that is comprised of a collection of vanes whose highly three-dimensional shape is selected to reduce rotor-stator and rotor-strut interaction noise while maintaining the aerodynamic and mechanical performance of the vane.

Abstract: A component for a gas turbine engine includes a rotor disk, a plurality of blade attachments, a plurality of retention flanges, and a plurality of retention tabs. The rotor disk has a plurality of slots formed in an outer surface thereof. Each blade attachment has an attachment region configured to be partially disposed within one of the slots. The plurality of retention flanges extend from the rotor disk outer surface, to thereby at least inhibit axial movement of the blade attachment, when the attachment region is fitted inside its corresponding slot. A retention tab extends from each attachment region and engages one of the retention flanges.

Abstract: A compressor includes an enhanced vaned shroud and is configured such that the flow area ratio is equivalent to that of a conventional, non-vaned shroud. The vaned shroud includes a plurality of airfoils that vary in thickness to obtain desired vibrational mode shapes and natural frequencies. A stiffening ring of limited axial extent is coupled to, and between, the airfoils, and the shroud is manufactured with a section of constant radius.

Abstract: A tip shroud assembly comprising a segmented annular shroud, each segment comprising an first arcuate member having a first radially inner surface and a circumferentially extending channel extending radially outward therefrom, and a second arcuate member received within the channel in spaced relation to the first arcuate member thereby defining a circumferentially extending passage therebetween, and a plurality of baffles located in the passage, each baffle extending from the first arcuate member to the second arcuate member.

Abstract: A tip shroud assembly comprising a segmented annular shroud, each segment comprising a radially outer surface, and a radially inner surface including a plurality of first holes defining a first row and a plurality of second holes defining a second row, with each of the rows extending circumferentially along the length of the segment and the first row in spaced relation to the second row. Spaced radially outward from the radially inner surface is a circumferentially extending plenum, and a plurality of first passages extend from one of the first holes to the plenum, and a plurality of second passages extend from one of the second holes to said plenum. The plenum communicates with the radially inner surface through each of the first and second passages, and the length of each of the first passages is at least three times the diameter of the first hole from which it extends.

Abstract: A tip shroud assembly comprising a segmented annular shroud, each segment comprising first, second and third arcuate members and a plurality of vane walls integral with the first second and third members, and each arcuate member has a radially inner surface, and the third arcuate member is in spaced relation to the first and second members, and each vane wall spans between the radially inner surface of the third arcuate member and the radially inner surfaces of the first and second members.

Abstract: The outer shroud of an axial flow compressor is treated to remove the low momentum flow adjacent the tips of the compressor blades in a judiciously located and sized passageway that removes the low momentum flow relative to the rotor blades at a location downstream of the blades' leading edge and returned at a location upstream of the point of removal. It being critical that no more than 12% of the total flow in the compressor rotor is removed for treatment. Anti-swirl vanes in the passageway serve to remove or reverse the swirl component from the removed low momentum flow. The intake is so designed that it selectively removes only the weak low momentum flow relative to the rotor and encourages the strong mainstream flow to remain in the main gas stream.