Abstract: A rotor including an internal fluid opening extending in a radial direction through the rotor and two ring seals disposed in opposed orientation on the rotor. Each of the two ring seals sealably and slidably engages the rotor. A stator is disposed around the rotor and the two ring seals and forms an external fluid opening extending in the radial direction through the stator. The stator includes two ring flanges disposed at axially distal ends thereof. Each of the two ring seals slidably contacts a respective one of the two ring flanges to form a mechanical sliding face seal.

Abstract: A rotary union includes a non-rotating machine component having a receiving counterbore, a media channel opening, and a control channel. A housing is positioned within the receiving counterbore and has a bore and a control chamber in fluid communication with the control channel. A non-rotating seal member is slidably and sealingly disposed within the bore in the housing and has a media channel in fluid communication with the media channel opening and the receiving counterbore. The non-rotating seal member can be selectively extended or retracted within the bore of the housing, such that selective engagement of a face seal is accomplished under different operating conditions of the rotary union.

Abstract: A rotary union includes a non-rotating machine component having a receiving counterbore, a media channel opening, and a control channel. A housing is positioned within the receiving counterbore and has a bore and a control chamber in fluid communication with the control channel. A non-rotating seal member is slidably and sealingly disposed within the bore in the housing and has a media channel in fluid communication with the media channel opening and the receiving counterbore. The non-rotating seal member can be selectively extended or retracted within the bore of the housing, such that selective engagement of a face seal is accomplished under different operating conditions of the rotary union.

Abstract: A gas turbine engine having a longitudinal centerline axis therethrough, including a fan section at a forward end of the gas turbine engine for producing a first compressed air flow; a first compressor positioned downstream of the fan section and in flow communication with at least a portion of the first compressed air flow, wherein the first compressor produces a second compressed air flow having a designated pressure; a combustor positioned downstream of the first compressor and in flow communication with second compressed air flow, wherein the combustor produces combustion products from a mixture of fuel and air; a first turbine positioned downstream of the combustor and in flow communication with combustion products, wherein the first turbine powers the first compressor by means of a first rotatable drive shaft connected therebetween; and, a second turbine positioned downstream of the first turbine and in flow communication with the combustion products exiting the first turbine, wherein the second turbine

Abstract: A gas turbine engine combustor can downstream of a pre-mixer has a pre-mixer flowpath therein and circumferentially spaced apart swirling vanes disposed across the pre-mixer flowpath. A primary fuel injector is positioned for injecting fuel into the pre-mixer flowpath. A combustion chamber surrounded by an annular combustor liner disposed in supply flow communication with the pre-mixer. An annular trapped dual vortex cavity located at an upstream end of the combustor liner is defined between an annular aft wall, an annular forward wall, and a circular radially outer wall formed therebetween. A cavity opening at a radially inner end of the cavity is spaced apart from the radially outer wall. Air injection first holes are disposed through the forward wall and air injection second holes are disposed through the aft wall. Fuel injection holes are disposed through at least one of the forward and aft walls.