Abstract: A turbine engine air control valve including a valve body having a fluid flow passage and a valve member disposed in the valve body. The valve member is configured to rotate about a rotation axis between a maximum flow position and a minimum flow position. The valve member includes a vane and a floating member operatively coupled to the vane. The floating member is configured to float relative to the vane, such that when the valve member is in the minimum flow position, the floating member is spaced apart from the valve body to form an annular flow gap that provides a controlled amount of minimum fluid flow across the valve member as the fluid flows through the annular flow gap.

Abstract: A balance bracket for a diffuser case of gas turbine engine is disclosed. In various embodiments, the balance bracket includes a first portion configured for mounting to a first boss on the diffuser case, a second portion configured for mounting to a second boss on the diffuser case, the second portion spaced a distance from the first portion, and a first undulating portion positioned intermediate the first portion and the second portion.

Abstract: A turbomachine fuel injector system includes an air distributor configured to be mounted to and contained within a casing and to provide air to mix with a fuel from one or more fuel distribution systems. The system includes a fuel manifold configured to be mounted indirectly to the casing such that the fuel manifold system is contained within the casing but is independent such that fuel manifold does not touch or directly mount to either an interior of the casing or touch the air distributor within the casing to prevent or reduce thermal transfer from the air distributor to the fuel manifold.

Abstract: A combustor (3) includes: a fuel nozzle configured to inject fuel; a tubular body (24) having a tubular shape in which a combustion region through which combustion gas flows is formed inside, and in which a plurality of slits (50) are formed extending in the circumferential direction at intervals in the circumferential direction; and throttle pieces (60) which are fitted into the slits (50), project radially inward from the inner circumferential side of the tubular body (24), and have a throttle face that extends along the flow direction of the combustion gas as it extends from the radially outer side inward.

Abstract: A particle separator includes a separator body in a primary fluid passageway of a machine. The primary fluid passageway includes one or more bleed holes through which a diverted portion of the fluid flowing in the primary fluid passageway toward a volume of the machine is diverted into an auxiliary flow passageway that bypasses the volume and directs the diverted portion of the fluid toward one or more other components of the machine. The separator body is coupled with the inner wall and/or outer wall of the primary fluid passageway. The separator body includes an upstream edge positioned to separate at least some particles carried by the fluid from the fluid as the diverted portion of the fluid bends around and flows over the at least one upstream edge of the separator body and into the auxiliary flow passageway.

Abstract: An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.

Abstract: A starter for a gas turbine engine includes a rotor shaft rotatable about an axis and includes an inner bore extending from an axial end of the rotor shaft with respect to the axis. A sun gear is on the rotor shaft. A lock nut is received against an axial end face of the sun gear and threadedly engaged with an outer diameter of the rotor shaft. A retainer is positioned to bias the nut against the axial end face and includes a projection portion threadedly engaged with the rotor shaft in the inner bore. A bolt through the projection portion is threadedly engaged with the rotor shaft.

Abstract: An oil heating system in a turbine engine such as an aircraft turbojet or turboprop main engines, or in an aircraft auxiliary power unit (APU). The turbine oil heating system includes a turbine engine oil circuit for conducting lubricating oil to the turbine engine, an electric starter generator oil circuit for conducting cooling oil from the electric starter generator, and an oil-to-oil heat exchanger connected with the engine oil circuit and connectable with the electric starter generator oil circuit, for transferring heat from the starter generator oil to the engine oil as to warm-up the engine oil during turbine engine motoring prior to actual starting sequence. A low cost and highly integrated system is therefore provided for reducing drag torque of a turbine engine prior to the starting phase.

Abstract: An aft heat shield for a fuel nozzle tip includes: an annular shield wall; an annular shield flange extending radially outward from an aft end of the shield wall; an annular baffle flange surrounding the conical section, and disposed such that an axial gap is defined between the shield flange and the baffle flange, the baffle flange including a radially outer rim extending axially forward therefrom; and a plurality of impingement cooling holes passing through the baffle flange and oriented to as to direct air flow towards the shield wall.

Abstract: A combustor reduces combustion vibration and the generation of nitrogen oxides and includes a burner to mix fuel with compressed air and to eject the mixture; a liner that is coupled to one end of the burner and forms a combustion chamber in which the fuel-air mixture is combusted to produce high-pressure gas; a transition piece to receive a flow of the high-pressure gas from the liner and to discharge the high-pressure gas to a turbine; a plurality of resonance modules disposed on an outer circumferential surface of the liner at positions spaced apart from each other along a circumferential direction of the liner; and a fuel supply unit coupled to each of the plurality of resonance modules and configured to supply fuel to each of the plurality of resonance modules. The resonance modules may be disposed on an outer circumferential surface of the transition piece instead of the liner.

Abstract: A cooling system with a thin walled cooling plate. The system includes an enclosure with a cover that defines an interior space and that has an open side. Temperature sensitive devices are contained in the interior space. A cooling plate closes the open side and includes an inner side with a surface that is substantially flat and that faces into the interior. The cooling plate defines a flow channel adjacent the inner side that is configured to channel a circulating fluid to remove heat from the interior space. The flow channel extends across substantially all of the opening. An outer side of the cooling plate may be anodized to block heat from entering the interior space through the cooling plate.

Abstract: A gas turbine engine comprises a combustor. The combustor comprises an annular combustor chamber formed between an inner liner and an outer liner spaced apart from the inner liner. An annular fuel manifold has fuel nozzles distributed circumferentially on the fuel manifold, the fuel manifold and fuel nozzles positioned entirely inside the combustion chamber.

Abstract: A method of securing a fuel injector seal assembly includes placing a fuel nozzle within a bore of a seal, and selectively limiting withdrawal of the fuel nozzle from the bore based on the circumferential position of the fuel nozzle relative to the bore.

Abstract: A combustor or augmentor of a gas turbine engine is provided. The combustor or augmentor includes a wall defining apertures and an interior having an inlet, an outlet and a mixing region between the inlet and the outlet and fuel injectors. The fuel injectors are respectively arrayed along the wall at corresponding apertures to inject fuel into the mixing region. Each fuel injector includes a fuel injector body defining an injection outlet through which fuel exits the fuel injector body toward the mixing region and a pintle. The pintle includes a first end, a second end and a pintle body extending between the first and second ends. At least one of the first and second ends is attachable to the fuel injector body to position the pintle body between the injection outlet and the mixing region.

Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a liner panel with a perimeter rail and a multiple of intermediate rails. A combustor for a gas turbine engine including a support shell and a multiple of liner panels mounted to the support shell via a multiple of studs, each of the multiple of liner panels having a multiple of intermediate rails to form a multiple of circumferential cavities.

Abstract: The present disclosure describes a micro gas turbine flameless heater, in which the heat is generated by burning fuel in a gas turbine engine, and the heater output air mixture is generated by transferring the heat in the gas turbine exhaust to the cold air drawn from the ambient environment. The present disclosure also describes component geometries and system layout for a gas turbine power generation unit that is designed for simple assembly, disassembly, and component replacement. The present disclosure also allows for quick removal of the rotating components of the gas turbine engine in order to reduce assembly and maintenance time. Furthermore, the present disclosure describes features that help to maintain safe operating temperatures for the bearings and structures of the gas turbine engine power turbine.

Abstract: An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first annular case that has a first body extending from a first end portion and a second annular case that has a second body extending along a longitudinal axis from a second end portion. The first end portion has a first flange. The first flange has at least one mounting assembly. The at least one mounting assembly has a first aperture dimensioned to receive a fastener and a first ramped surface that extends axially from the first aperture. The second end portion includes at least one flange that defines a receptacle dimensioned to receive the first end portion and a second aperture dimensioned to receive the fastener and a second ramped surface.

Abstract: An annular combustion chamber (10) having a first annular wall (12) and a second annular wall (13) that are coaxial about an axis (X), a chamber end wall (14) connecting together the first and second walls (12, 13), and a plurality of injectors (16), the first wall (12) including first air feed holes (18) downstream from the injectors (16), the combustion chamber (10) being characterized in that for at least a first one of said injectors (16), at least three of the first holes (18) sharing the first injector as their closest injector are situated at equal distances (D) from the first injector (16).

Abstract: A disclosed turbofan engine includes a first spool including a first turbine; a second spool including a second turbine disposed axially forward of the first turbine, a first tower shaft engaged to the first spool, a second tower shaft engaged to the second spool, and a superposition gearbox including a sun gear, a plurality of intermediate gears engaged to the sun gear and supported in a carrier and a ring gear circumscribing the intermediate gears. The second tower shaft is engaged to drive the sun gear. A starter is selectively coupled to the sun gear through a starter clutch. A first clutch selectively couples the first tower shaft to the ring gear and a second clutch selectively couples the ring gear to a static structure of the engine. An accessory gearbox is driven by an output of the superposition gearbox.

Abstract: A turbine combustor assembly includes a fuel/air mixer assembly having a plurality of fuel/air mixer elements and a fuel injector coupled to the fuel/air mixer assembly. Each of the fuel/air mixer elements includes: a fuel/air mixer body having an internal cavity extending axially between an air inlet and an air outlet; and a prefilmer residing within an interior cavity of the fuel/air mixer body, the prefilmer including an axial inner air flow passage extending coaxially with an axial centerline of the internal cavity of the fuel/air mixer body and a radial fuel injection port into the air flow passage. The fuel injector is arranged to direct fuel into a plurality of the fuel/air mixer elements via the fuel injection port of the prefilmer of each fuel/air mixer element.