Abstract: An auxiliary power unit (APU) compartment air inlet system seals, via one or more inlet doors driven by a single actuator, an APU compartment, and isolates the APU inlet and cooling system inlets from each other. The system includes either one or two inlet doors, depending on the number of ram air inlets formed in the APU compartment. In either instance, however, a single actuator is used to move the inlet door(s) between open and closed positions.

Abstract: A combustion chamber having a burner and a burner insert surrounding the burner while leaving a gap open towards the combustion chamber interior is provided. The burner insert comprises a carrier and a burner insert wall located in front of the carrier towards the combustion chamber interior, wherein a flow passage connected to a cooling-fluid source is formed between the carrier and the burner insert wall. The flow passage opens out into the gap between the burner and the burner insert and is otherwise sealed off from the combustion chamber interior.

Abstract: In this cooling structure, a cooling flow path, which is meandering around a flow direction of a high temperature combustion gas, is provided in a structural body. The cooling flow path has an inflow path for a cooling air formed inside of the structural body; at least one straight flow path provided with intervals with respect to an axial line; and a turning flow path for communicating the end portions of the inflow path with the straight flow path or communicating with the end portions of the straight flow paths one after another.

Abstract: Apparatus for protecting a feed injector and methods of assembly are provided. In one aspect, a method of assembling a feed injector cooling apparatus includes coupling a coolant source in flow communication with a mounting flange, coupling the mounting flange to a first end of a sheath, wherein the sheath circumscribes a feed injector barrel, and coupling a cap to a second end of the sheath, wherein the cap includes a center port through which a feed injector tip projects into a gasifier.

Abstract: A thermal management system for a gas turbine engine includes a cooling airflow which enters through an air filter portion of a forward cover for filtration of particulate which may result in FOD to a rotational system of the engine. Filtered cooling airflow flows along a rotor shaft over and through a forward bearing, over and through a permanent magnet generator, then over and through an aft bearing to provide thermal management. Commensurate therewith, the cooling airflow atomizes and communicates a lubricant to the bearings. From the aft bearing, the cooling airflow merges with a primary airflow path from an intake which generally surrounds the forward cover.

Abstract: The invention concerns a precooler (30) having an annular cross-sectional shape about the axis (L-L) of the pod and arranged inside the rear part (10R) of the inner shroud (10) in external contact with the cold flow (9) exiting the fan duct channel (13) and in close contract with the cooling air stream (29) drawn from said cold flow (9).

Abstract: A turbine nozzle includes first and second vanes joined to outer and inner bands. The vanes include outboard sides defining outboard flow passages containing axial splitlines, and opposite inboard sides defining an inboard flow passage without axial splitline. The two vanes include different cooling circuits for differently cooling the inboard and outboard vane sides.

Abstract: A combustion chamber suitable for a gas turbine engine is provided with at least one Helmholtz resonator having a resonator cavity and a resonator neck in flow communication with the chamber interior. The resonator neck is provided with at least cooling holes extending through its wall for improved damping and cooling, at least one of the holes is directed towards the resonator cavity.

Abstract: A gas turbine engine is provided comprising a compressor, a fuel supply apparatus, a combustor, and a turbine. The fuel supply apparatus comprises a fuel source, a cooling apparatus including a heat exchanger and structure for defining a first path for fuel to travel from the fuel source to the heat exchanger and a second path for fuel to travel away from the heat exchanger. The combustor functions to receive the compressed air from the compressor and the fuel from the heat exchanger, combine the air and fuel to create an air/fuel mixture and ignite the air/fuel mixture to create combustion products. The cooling apparatus further comprises structure coupled to and extending between the heat exchanger and at least one of a plurality vanes in the turbine for circulating a coolant fluid through at least one vane and the heat exchanger. In another embodiment, pipe supply structure extends from a fuel source through an end section of a turbine casing.

Abstract: Means for cooling a bearing assembly supporting a rotor stage of a gas turbine engine after engine shutdown. The engine comprises a combustion section, a compressor for the delivery of air to the combustion section, and a bearing assembly supporting a rotor stage. The means for cooling a bearing assembly comprises a means operable to generate a signal representative of turbine duct temperature immediately prior to engine shutdown, a means for determining the duration for cooling after engine shutdown as a function of the signal representative of turbine duct temperature, and the compressor operable as a cooling means to deliver cooling air to the rotor stage after engine shutdown. Thereby the amount of heat conducted to the bearing assembly is limited such that the temperature of the bearing assembly is limited to below a predetermined temperature.

Abstract: An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal may include an inner housing and an outer housing. The inner housing or the outer housing, or both, may be shortened relative to conventional clips and may include a cooling channel proximate to a point of attachment to the combustor basket.

Abstract: A system is provided for directing air from plural compressor ports to provide cooling and/or sealing air to an associated turbine site. A first flow from a pressure stage of the compressor has a first pressure and temperature. A second flow from another pressure stage of the compressor has a second pressure and temperature. The first and second pressures/temperatures are different. An ejector has two inlets for receiving the first and second flows, and output for combining the first and second flows into a third flow. The pressure and temperature of the third flow are different from the first and second pressures and temperatures. A bypass line is connected between the first flow and the third flow, and provides a bypass flow. A mixer combines the bypass flow and the third flow into a fourth flow. The fourth flow has a pressure and temperature intermediate the pressure and temperature of the bypass flow and the third flow. The mixer comprises inner and outer sections.

Abstract: The invention relates to a combination power plant which is embodied as a single shaft, power plant, essentially consisting of a gas turbine, a steam turbine and a generator which is connected therebetween. A coupling is arranged between the generator and the steam turbine, and at least one drive device, which is used to drive the single-shaft power plant, is also provided. The coupling is uncoupled during a turning operation and a control unit, which is used to control the rotational speed of the steam turbine, is provided.

Abstract: A gas turbine power generator plant, intended to reduce its noise by making small the intake and exhaust outlets of the cooing air channel of a case, comprises an engine core in which a turbine, a compressor and a generator are installed on the same axis, a combustor for burning air for combustion compressed by the compressor and supplying the air to the turbine, a radiator for cooling a coolant or a lubricant, a cooling fan for ventilating the radiator with cooling air, an electric power converter for converting electric power generated by the generator, and the case for housing these constituent elements. And, a combustion air channel passing the compressor, the combustor and the turbine and a cooling air channel passing the radiator, the cooling fan and the electric power converter are formed as mutually independent channels from intake to exhaust.

Abstract: High performance propellants flow through specialized mechanical hardware that allows for effective and safe thermal decomposition and/or combustion of the propellants. By integrating a sintered metal component between a propellant feed source and the combustion chamber, an effective and reliable fuel injector head may be implemented. Additionally the fuel injector head design integrates a spark ignition mechanism that withstands extremely hot running conditions without noticeable spark mechanism degradation.

Abstract: A gas turbine engine includes turbine blades having film cooling holes at an outer face of an airfoil wherein the film cooling holes are designed to be better filled with air. In a disclosed embodiment, the film cooling holes include a meter section extending along a direction having a main component extending from a blade tip to a blade root. In addition, a diffused section communicates with the meter section at a face of the airfoil. The diffused section is spaced toward the blade tip from the meter section. In this manner, centrifugal force ensures the diffused section is also filled with air.

Abstract: The combustion chamber (10) comprises a chamber endwall (16) which takes the form of a substantially frustoconical component consisting of a succession of adjacent planar portions (166). The invention can be applied to a combustion chamber (10) of a turbine engine (2).

Abstract: Disclosed is a structural frame for a gas turbine engine comprising an integral fluid reservoir and air/fluid heat exchanger. A central hub includes a reservoir for storing a fluid and an outer rim circumscribes the hub. A heat exchanger is fluidly coupled to the reservoir and is in simultaneous communication with the fluid and an air stream.

Abstract: A method for assembling a gas turbine engine assembly that includes mounting a gas turbine engine including an inlet and an exhaust within a module that includes an inlet area, an exhaust area, and an engine area extending therebetween, such that the gas turbine engine is housed within the module, coupling a first deflector within the module engine area such that when cooling air is channeled past the deflector, the deflector induces a substantially helically-shaped cooling air flowpath around a periphery of the gas turbine engine, and coupling an exhaust duct to an outlet of the module exhaust area.

Abstract: The accessory gearbox (AGB) has at least one coolant passage between the AGB and the accessory for externally cooling the accessory without coolant flow inside the accessory.

Abstract: A turbine nozzle (2) that, among components constructing a turbine, reaches particularly high temperature is efficiently cooled with a relatively simple structure. A double casing structure in which a turbine casing (7) is provided outside a turbine shell (5) is formed. The turbine casing (7) functions as a flow path (24) for compressed air (20?21) before combustion. The turbine shell (5) covers a turbine nozzle (2) and a radial turbine impeller (3) and forms flow paths (15, 16) for combustion gas (10?11?12?13). The compressed air (21) before combustion flowing in the flow path (24), for compressed air, having air-tightness between itself and the outside air is blown to the turbine nozzle (2) through a through-hole (51) penetrating both wall surfaces of the turbine shell (5). By this, the turbine nozzle (2) is cooled and the compressed air used to cool the turbine nozzle is made to flow toward the turbine impeller (3).

Abstract: A method and device for improved pressure balancing in a bearing chamber pressurization system for gas turbine engines employ a partition member to substantially separate first and second air-oil seals of the bearing housing.

Abstract: A control arrangement (10) comprises a first selectable controller (12) for controlling an action, and a second selectable controller (14) for controlling the action. The arrangement also includes a selector (22) for selecting one of the controllers (12, 14) to control the action. The arrangement (10) further includes a first heat exchanger (16) associated with the first controller (12) to effect a transfer of heat between the first controller (12) and the first heat exchanger (16). The arrangement also includes a second heat exchanger (18) associated with the second controller (14) to effect a transfer of heat between the second controller (14) and the second heat exchanger (18).

Abstract: An auxiliary power unit (APU) includes a compressor, a turbine, a combustor, and a starter-generator unit all integrated within a single containment housing. The turbine has an output shaft on which the compressor is mounted, and the starter-generator unit is coupled to the turbine output shaft without any intervening gears. The rotating components are all rotationally supported within the containment housing using bearings that do not receive a flow of lubricating fluid.

Abstract: A fastener shield for use in a fluid flow path within a gas turbine engine for reducing fluid drag and heating generated by fluid flow over a plurality of circumferentially spaced fasteners. The fastener shield has a radially-extending, downstream-facing mounting flange with a plurality of circumferentially spaced bolt holes positioned to receive respective engine mounting bolts therethrough and to attach the mounting flange to elements of the turbine engine. A curved, upstream-facing fastener shield cover is positioned in spaced-apart relation to the mounting flange for at least partially covering and separating an exposed, upstream-facing portion of the bolts from the fluid flow to thereby reduce drag and consequent heating of the bolts.

Abstract: A forced air cooling system for an APU comprising at least an oil cooler, a plenum in fluid communication with the oil cooler, and a compressor rotated by a rotating shaft of the APU such that the compressor and rotating shaft rotate at a same speed, the rotating compressor inducing a cooling air flow through the oil cooler. A method for cooling an auxiliary power unit is also provided.

Abstract: An ignition device assembly for a gas turbine engine combustor includes a body and a shroud. The body extends from an inlet end to an outlet end, and the shroud extends circumferentially around at least a portion of the body, and axially from a first end to a tip end. The shroud includes a tip portion and a body portion. The body portion includes a plurality of metering openings and a plurality of first outlet openings. The plurality of metering openings are for channeling cooling air to the ignition device body, and the plurality of first outlet openings are for channeling spent cooling air from the ignition device body. The tip portion includes a plurality of discharge openings extending therethrough for channeling cooling from the ignition device body. The plurality of first outlet openings are between the shroud tip portion and the plurality of shroud metering openings.

Abstract: A mounting system for mounting an air-cooled device to a mount, the device having a mounting flange and a cooling air outlet radially inward of an outer periphery of the device, the mounting flange adapted to cooperate with the mount, where the mounting system has a cooling air exhaust collection shroud adapted to surround the device and at least a portion of the mount, the shroud having a discharge outlet.

Abstract: A method to ventilate a rotary machine housed in a compartment having a ventilation air inlet and air exhaust, a variable speed ventilation fan and a temperature sensor, wherein the method includes: sensing a temperature level of the rotary machine; applying the sensed machine temperature level to a controller for the fan; drawing ventilation flow through the compartment and over the machine; determining whether the sensed machine temperature level is above a desired temperature level of the rotary machine, wherein the desired temperature level is determined by the controller, and the controller setting an operational condition of the fan to increase the ventilation flow through the compartment if the sensed machine temperature level is above the desired temperature level.

Abstract: A method facilitates assembling a gas turbine engine. The method comprises coupling a combustor including a dome assembly and a combustor liner that extends downstream from the dome assembly to a combustor casing that is positioned radially outwardly from the combustor, coupling a fuel injector including a fuel inlet and an air inlet to the combustor casing such that the fuel injector extends axially through the dome assembly such that fuel may be discharged from the primer nozzle into the combustor, and coupling the air inlet to an air source such that cooling air received therethrough is circulated through the fuel injector to facilitate cooling the fuel injector.

Abstract: An air intake for an aircraft forms a first airflow channel (8) for feeding fresh air into the aircraft, and a second airflow channel (2) for feeding cooling air to an auxiliary power unit (AP). These first and second airflow channels are so positioned relative to each other that respective channel inlets or flow cross-sectional areas can be opened and closed by a single seesaw rocker (4) which is journaled or hinged between its ends to the aircraft body in such a position that one end (4A) of the seesaw rocker (4) can close the first channel (2) while the other rocker end (4B) simultaneously closes the second channel (8). The seesaw rocker (4) is driven by a motor responsive to the operation of the auxiliary power unit. When the auxiliary power unit operates, both channels (2, 8) are open. When the auxiliary power unit does not operate both channels (2, 8) are closed.

Abstract: An assembly for ventilating a stator ring having branched pipes that include feed pipes, distributors, and a plurality of manifolds adjacent to the stator ring and provided with drilled holes. The distributors connect the feed pipes to the plurality of manifolds, and the plurality of manifolds include pairs of half-shells, each of the half-shells including an end plate having an opening and a rim surrounding the end plate, and the half-shells in each of the pairs being joined to each other at the rims. The distributors include ducts mounted between adjacent ones of the plurality of manifolds and have open ends fitted into openings of the end plates and have abutment portions to the end plates.

Abstract: A fluid flow actuated valve for controlling the fluid flow in a conduit comprises a support structure adapted to be mounted within the conduit and at least one flap member pivotally mounted to the support structure. The at least one flap member is pivotable between an first position for a minimum fluid flow and a second position for a maximum fluid flow. A torsion spring is attached to the at least one flap member to urge the same to pivot against a fluid pressure differential, from the first position to the second position when the fluid pressure differential is smaller than a predetermined level.

Abstract: A mounting system, for installing a starter-generator to an accessory housing, where the starter-generator has a mounting end with a connecting flange and a cooling air outlet radially inward of a peripheral starter-generator housing edge, and where the accessory housing has a matching connecting flange radially inward of a peripheral accessory housing edge. The mounting system includes a cooling air outlet collection shroud enveloping the peripheral starter-generator housing edge and the peripheral accessory housing edge, the shroud having a discharge outlet. A V-band clamp releasably secures the connecting flanges together and is enveloped within the shroud in a compact mounting system that collects and discharges the exhausted cooling air.

Abstract: An anti-condensation device for a flame sensor (10) of a combustion chamber (12), wherein the sensor (10) is disposed outside the combustion chamber (12) and determines the presence of the combustion flame by means of an aperture (14) provided in a wall of the chamber (12); the device comprises at least two tubular structures (22, 24), one of which (24) surrounds the other (22) at least partially, an annular space in which air flows being provided between these two structures (22, 24).

Abstract: An injector includes a plurality of flat, circular plates which provide fuel delivery and cooling of the injector. Fuel delivery passages in the plates have swirl chambers and spray orifices which are formed by chemical etching. A pair of fuel delivery plates define a fuel cavity therebetween, and include a plurality of radially-outwardly extending spokes, with the spokes from one fuel plate in adjacent, surface-to-surface relation with opposing spokes from the adjacent fuel plate. A fuel passage is defined between each of the opposing spokes, leading from the fuel cavity to a fuel outlet opening at the distal end of each spoke. A fuel tube delivers fuel to the fuel cavity between the plates, from where the fuel is then directed through the outlet openings. Downstream plates shape the fuel into appropriate sprays for ignition. An upstream cooling plate assembly directs air against the upstream fuel plate, and radially outwardly along the spokes of the upstream plate.

Abstract: A system for cooling at least one gas turbine liquid fuel component located in a high temperature environment to eliminate coking in the component is disclosed. The system includes a sleeve surrounding the liquid fuel component, a device for providing a current of cool air, and a conduit connected between the cool air device and the sleeve to direct the current of cool air into the sleeve to cool the liquid fuel component. The system can also include a manifold connected to the conduit and a plurality of second conduits for connecting the manifold to a plurality of sleeves surrounding a plurality of liquid fuel components, each sleeve being connected to a corresponding second conduit. Each sleeve includes a plurality of spacing devices for centering the sleeve around the at least one liquid fuel component so as to form an annulus between the sleeve and the liquid fuel component through which the current of cool air flows.

Abstract: A passive cooling system for an auxiliary power unit (APU) installation on an aircraft is provided. The system is for an auxiliary power unit having at least a compressor portion of a gas turbine engine and an oil cooler contained separately within a nacelle. The system includes the auxiliary power unit housed within the nacelle of the aircraft, an engine exhaust opening defined in the aft portion of the nacelle and communicating with the gas turbine engine, at least a first air inlet duct communicating with a second opening defined in said nacelle and with said compressor portion and the oil cooler is located within a second duct communicating with an opening other than the engine exhaust opening of said nacelle and with the engine exhaust opening. Exterior cooling air and engine exhaust ejected through said engine exhaust opening entrain cooling air through said second duct to said oil cooler, and thus provide engine oil cooling. An exhaust eductor is also provided.

Abstract: Apparatus for maintaining the temperature of a component of a gas turbine engine below a predetermined maximum working temperature comprises a reservoir for a cooling fluid having a boiling point below the working temperature and in which the component is immersed or with which it is in contact. At least two heat exchangers are associated with the reservoir and operable to effect condensation of vaporised cooling fluid and return of same to the reservoir. Preferably the apparatus is a closed system incorporating three heat exchangers respectively adapted to effect heat exchange with engine fuel, compressed air derived from a fan or low pressure compressor of the engine and ambient air. Means may advantageously be provided to ensure return of condensed cooling fluid to the reservoir when the attitude of the reservoir is altered as a result of aircraft manoeuvres.

Abstract: An air intake for an aircraft forms a first airflow channel (8) for feeding fresh air into the aircraft, and a second airflow channel (2) for feeding cooling air to an auxiliary power unit (AP). These first and second airflow channels are so positioned relative to each other that respective channel inlets or flow cross-sectional areas can be opened and closed by a single seesaw rocker (4) which is journaled or hinged between its ends to the aircraft body in such a position that one end (4A) of the seesaw rocker (4) can close the first channel (2) while the other rocker end (4B) simultaneously closes the second channel (8). The seesaw rocker (4) is driven by a motor responsive to the operation of the auxiliary power unit. When the auxiliary power unit operates, both channels (2, 8) are open. When the auxiliary power unit does not operate both channels (2, 8) are closed.

Abstract: A gas turbine system comprises a compressor that takes in suction air on the inlet side and compresses it to compressor end air that is available on the outlet side, a combustor in which a fuel is burned by using the compressor end air while resulting in the formation of hot gas, as well as a turbine in which the hot gas is expanded while providing work output. In a method for cooling this gas turbine system, compressed air is removed from the compressor, is fed as cooling air for cooling inside an internal cooling channel through thermally loaded components of the combustor and/or the turbine, is then recooled and subsequently compressed and added to the compressor end air. The influence of the cooling on the efficiency of the system is minimized by the fact that at least part of the compressor end air is used to recool the cooling air.

Abstract: An injector includes a plurality of flat, circular plates which provide fuel delivery and cooling of the injector. Fuel delivery passages in the plates have swirl chambers and spray orifices which are formed by chemical etching. A pair of fuel delivery plates define a fuel cavity therebetween, and include a plurality of radially-outwardly extending spokes, with the spokes from one fuel plate in adjacent, surface-to-surface relation with opposing spokes from the adjacent fuel plate. A fuel passage is defined between each of the opposing spokes, leading from the fuel cavity to a fuel outlet opening at the distal end of each spoke. A fuel tube delivers fuel to the fuel cavity between the plates, from where the fuel is then directed through the outlet openings. Downstream plates shape the fuel into appropriate sprays for ignition. An upstream cooling plate assembly directs air against the upstream fuel plate, and radially outwardly along the spokes of the upstream plate.

Abstract: An efficient, economical, reliable method for reducing aircraft fuel tank explosion potential that can easily be manufactured or retrofitted to existing aircraft systems. Ducting means to connect an aircraft's propulsion or auxiliary power gas turbine jet engine air intake suction area to the aircraft's fuel tank ullage area to effect continuous or selective suction operation for removal of potentially explosive fuel fume-vapors and replacement of the fume-vapors with outside or temperature controlled outside air with lower-oxygen content air or inert substances to reduce fuel tank explosive and flammability potential. Similarly, ducting is provided from engine intake suction area to areas around the exterior of the fuel tank to suction excessive heat away from the tank and replace it with cooler outside air, mechanically conditioned air or cabin/flightdeck air to reduce the explosive and flammability potential.

Abstract: In a gas turbine power plant system having an air chiller for lowering the temperature of inlet air, a compressor for compressing the inlet air, a combustor for combusting the compressed air and fuel and a power turbine for providing useful power, a method and apparatus for chilling water delivered to the air chiller is provided, having a thermal water storage tank for storing chilling water, the tank having a bottom portion and a top portion, and a bottom inlet and a bottom outlet and a top inlet and a top outlet. A charge cycle is provided wherein the tank is filled with chilled water, and a discharge cycle is provided wherein the chilled water is fed to the air chiller, thereby chilling the inlet air to the power turbine.

Abstract: A turbine casing supports a row of nozzle vanes through which are flowable hot combustion gases. A baffle surrounds the casing to define a cooling duct. A nacelle surrounds the turbine casing to define a bay having an inlet for receiving bay air, and an outlet for discharging the air. The cooling duct includes an inlet which receives the bay air for flow along the turbine casing for selective cooling thereof.

Abstract: A system is provided for cooling the undercowl environment of a gas turbine engine having a high pressure compressor and a core gas stream. An electronically controlled compartment cooling valve is controlled as a function of corrected fan speed, altitude, ambient conditions, extreme hot day temperatures and the aircraft environmental control system. A cooling manifold distributes cooling air in the undercowl environment. A regulator, such as an on-off control valve, modulates the amount of undercowl cooling flows as a function of any of a variety of conditions.

Abstract: A combustion turbine system of this invention includes a compressor, a combustor, a turbine section, an external blower, an electrical generator and a prime mover for powering the blower and the compressor. The compressor produces a compressed air that mixes with fuel in the combustor to produce a hot gas. This hot gas is sent through the turbine section of the combustion turbine system to drive a rotor. The electrical generator may be coupled to the rotor, so that rotation of the rotor causes operation of the electrical generator. The rotor may also be coupled to the compressor, so that the rotation of the rotor also drives the compressor. The blower of this invention is external to the generator and provides a cooling medium for the electrical generator. The prime mover is coupled to the external blower so that it can power the blower and provide the cooling medium for the electrical generator. In addition, the prime mover is selectively connectable to the rotor, so that it can turn the rotor.