Abstract: A method for forming a heat exchanger plate includes providing a precursor having a body with a first face and a second face opposite the first face and at least one internal passageway; and pluralities of first and second fin precursors respectively protruding from the first and second faces. First and second fin height profiles are formed by removing material from the respective fin precursors via wire electro-discharge machining.

Abstract: Cabin outflow temperature control systems and methods for use on aircraft are described. The systems include an aircraft cabin, a heat load source, a heat exchanger configured to receive cabin outflow air from the aircraft cabin and heat load discharge air, the heat exchanger configured to enable thermal transfer from the heat load discharge air to the cabin outflow air to generate high temperature cabin outflow air and low temperature discharge air as outputs from the heat exchanger, and one or more downstream operation systems configured to receive the high temperature cabin outflow air and perform a downstream operation using said high temperature cabin outflow air.

Abstract: A liquid rocket engine cools a thruster body by pumping propellant through cooling channels integrated in the thruster body between internal and external surfaces. One or more of the cooling channel surfaces has a variable depth along a thrust axis to mix propellant flow and destroy thermal stratification, such as a depth that varies with a repeated contiguous sinusoidal form along the thrust axis. Fuel passed through the cooling channels injects from the combustion chamber wall towards a central portion of the combustion chamber to cross impinge with oxygen injected at the combustion chamber head so that a toroidal vortex forms to enhance propellant mixing.

Abstract: A combined cycle power plant is capable of improving power output and power generation efficiency by cooling intake air supplied to a gas turbine. The plant includes a gas turbine power generation system, an operating fluid power generation system, and a cooling system. The gas turbine power generation system includes an air compressor for compressing air supplied through an air incoming path, a gas turbine for generating rotary power by burning a mixture of fuel and the air compressed by the air compressor, and a first generator for generating electricity by using the rotary power of the gas turbine. The operating fluid power generation system heats an operating fluid by using combustion gas discharged from the gas turbine and generates electricity using the heated operating fluid. The cooling system cools air supplied from the air compressor by supplying the operating fluid to an upstream side of the air compressor.

Abstract: A method for operating a gas turbine plant with gaseous fuel, which is conveyed to the gas turbine plant through a gas line, burnt in a combustion chamber and then supplied to a gas turbine. At least one valve for controlling the flow of the fuel to the combustion chamber is installed in the gas line, a critical opening position being defined for the valve. To provide an improved method for operating a gas turbine plant in which the power of the gas turbine plant is kept at a maximum for as long as possible in the event of insufficient pressure in the gas line, a temperature of the fuel in the gas line is reduced when the valve is about to exceed the critical opening position.

Abstract: An injector of a propellant combustion member, the injector including a first feed and a second feed; the first feed being connected to a plurality of feed chimneys arranged around a longitudinal axis; the second feed being configured so as to feed an injection chamber; and the injection chamber being connected to a plurality of feed sheaths with injection orifices, each feed chimney being surrounded by a coaxial feed sheath; the injector including a takeoff chamber connected to a takeoff duct for taking off the second propellant, the takeoff chamber being arranged in such a manner as to take off the second liquid propellant from the injection chamber; and it is configured to achieve uniform injection of the second propellant via the injection orifices.

Abstract: An airfoil including a spar and a cover sheet. Standoffs, a leading edge wall, and a separator wall extend away from an outer surface of the spar. The standoffs are arranged to define leading grooves disposed at the pressure side of the leading edge. The cover sheet is coupled to the leading edge wall and the standoffs over the leading grooves to define cooling passageways. The cooling passageways are in communication with one or more inlet ports formed in the spar, which are in communication with a plenum disposed within the spar. The cover sheet is arranged to define outlet ports or a slot in communication with the cooling passageway. Cooling air is delivered from the cooling air plenum through the inlet port for impingement cooling at the cover sheet, and traverses downstream through the cooling passageway to the outlet ports or slot for film cooling of the leading edge.

Abstract: A gas turbine engine combustor basket has nested outer and inner liners that are separated by a gap at their respective distal downstream ends for passage of cooling air between the liners. Radially inwardly projecting platefins formed on an inner circumferential surface of the outer liner maintain the cooling air passage gap. In some embodiments effusion cooling through holes are formed in the inner liner outer circumference, oriented in the air passage gap between the fins, so that cooling air passes through the effusion holes into the cooling air passage gap.

Abstract: A pressure gain combustor comprises a detonation chamber, a pre-combustion chamber, an oxidant swirl generator, an expansion-deflection (E-D) nozzle, and an ignition source. The detonation chamber has an upstream intake end and a downstream discharge end, and is configured to allow a supersonic combustion event to propagate therethrough. The pre-combustion chamber has a downstream end in fluid communication with the detonation chamber intake end, an upstream end in communication with a fuel delivery pathway, and a circumferential perimeter between the upstream and downstream ends with an annular opening in communication with an annular oxidant delivery pathway. The oxidant swirl generator is located in the oxidant delivery pathway and comprises vanes configured to cause oxidant flowing past the vanes to flow tangentially into the pre-combustion chamber thereby creating a high swirl velocity zone around the annular opening and a low swirl velocity zone in a central portion of the pre-combustion chamber.

Abstract: A cylindrical shift converter (4) is disposed within an annular heat exchanger (28, 24) which has an outer wall (5). A plurality of spiral rods (90) create a plurality of spiral gas passages (26a) between the outer wall and a thin shell (92). The outer diameter of the thin shell is at least about 3/16 inch (about 4 mm) less than the inner diameter of an inner wall (20) of an annular hydrodesulfurizer (10), to facilitate inserting the shift converter and heat exchanger into the hydrodesulfurizer to form a unitized assembly (2). The spiral passages open into the hydrodesulfurizer.

Abstract: An aft frame and a method for cooling an aft frame are disclosed. In one embodiment, an aft frame for a transition piece in a combustor is disclosed. The combustor includes the transition piece and an impingement sleeve at least partially defining a flow path therebetween. The aft frame includes a body and a generally radially extending cooling passage defined in the body, the cooling passage comprising a first end configured to accept a coolant. The aft frame further includes an exhaust passage defined in the body, the exhaust passage including a first end in communication with the cooling passage and a second end configured for communication with the flow path for flowing the coolant therethrough.

Abstract: A combustor having a combustion chamber is provided with an external flow sleeve and a combustor liner surrounding the combustion chamber. A plurality of flow channels are provided on the combustor liner and a plurality of nozzles are disposed at predetermined locations on the flow channels. The locations of the nozzles are selected to provide different mixing times for fuel injected through the nozzles.

Abstract: An inlet air conditioning system for a gas turbine includes an inlet duct for the with an air flow path to provide inlet air to the gas turbine; evaporative cooling media disposed in the air flow path; a water chiller; and a circulation pump that circulates water through the water chiller and the evaporative media in series. The chiller is configured to chill the water to below ambient wet-bulb temperature before the water is circulated to the evaporative cooling media. A power plant includes a gas turbine including a compressor, a combustion system, and a turbine section; a load; and the inlet air conditioning system.

Abstract: An air intake system for a gas turbine includes one or more coils in airflow communication with an inlet arrangement. Each coil is constructed and arranged to have a respective upstream face velocity that is intended to be within 20% of the other coils. Each coil utilizes a working fluid of a predetermined temperature range conveyed there through and a plurality of spaced fins. The fins are spaced apart to permit air to flow between adjacent fins as air flows through the coil. At least one of the coils has a number of fins per inch that is different from the number of fins per inch of the other coils. Alternatively, each individual coil has at least one section with fewer or greater numbers of fins per inch that the other sections of that coil.

Abstract: A closed circuit fuel heating system is provided for heating at least two types of fuel. The heating system includes a heat transfer subsystem disposed in a gas turbine system exhaust. A first heat exchange subsystem is coupled to a first fuel source and the heat transfer subsystem. The first heat exchange subsystem is provided with a control component for controlling a flow of a working fluid through the first heat exchange subsystem. A second heat exchange subsystem may be coupled to a second fuel source and the heat transfer subsystem. The second heat exchange subsystem is provided with a control component for controlling a flow of the working fluid through the second exchange subsystem. A subsystem for controlling the temperature of the working fluid is also provided.

Abstract: A method of recovering heat energy from a cooling medium used to cool hot gas path components in a turbine engine includes cooling one or more hot gas path components with the cooling medium; supplying spent cooling medium used to cool the one or more hot gas path components to a heat exchanger; supplying air (e.g., compressor discharge air) to the heat exchanger so as to be in heat exchange relationship with the spent cooling medium and thereby add heat to the compressor discharge air; and supplying the air heated in the heat exchanger to at least one combustor.

Abstract: A gas turbine engine with a fuel air heat exchanger located in the high pressure plenum. The heat exchanger includes at least one air conduit and at least one fuel conduit in heat exchange relationship with one another, with a fuel flow communication between a fuel source and fuel distribution members of the combustor being provided at least partly through the at least one fuel conduit, and the at least one air conduit defining a fluid flow communication between the high pressure plenum and an engine component to be cooled by the compressed air.

Abstract: A hybrid electric rotary engine is provided having a pair of rotors separated by a divider and configured for rotation in opposite directions, a timing gear engaged between the inner faces of the rotors, and at least one pair of slanted rotor openings in the rim of each rotor for alignment with at least one pair of slanted divider openings to form a pair of combustion chambers in communication with at least one pair of exhaust chambers for venting of exhaust and to provide rotational thrust.

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes a fan. A geared architecture is configured for driving the fan. A turbine section is configured for driving the geared architecture. A thermal management system that includes a first fluid circuit and a second fluid circuit that manage heat generated in at least a portion of the gas turbine engine. A first heat exchanger is incorporated into each of the first fluid circuit and the second fluid circuit. A second heat exchanger is incorporated into the first fluid circuit. A valve controls an amount of a first fluid that is communicated to the first heat exchanger and the second heat exchanger. A controller is configured to control a positioning of the valve.

Abstract: A heat exchanger has a first passage to be connected to a source of fuel. The heat exchanger has an outlet to communicate the fuel downstream. A second passage connects to a source of air. The air passes adjacent to the first passage to heat fuel in the first passage. A jet pump is positioned downstream of the second passage to receive air from the second passage. The jet pump includes a tap connected to a housing compartment to drain fluid from the compartment. A method is also disclosed.

Abstract: In an aircraft including a gas turbine engine, a system for cooling the gas turbine engine includes a tank provided in a wing of the aircraft, the tank being configured to store a cooling fluid supply; and a heat exchanger provided in the gas turbine engine configured to exchange heat from the compressor discharge air to the cooling fluid.

Abstract: A gas turbine can efficiently be cooled by using steam, without using high-pressure steam generated in an exhaust-heat recovery boiler and without decreasing the high-pressure steam generation. This cooling system is provided with a gas turbine; an exhaust-heat recovery boiler having a high-pressure system that generates high-pressure steam by means of heat exchange with exhaust heat from the gas turbine, a high-pressure drum that supplies water and steam to the high-pressure system, a medium-pressure system that generates medium-pressure steam by means of heat exchange with the exhaust heat from the gas turbine, and a medium-pressure drum that supplies water and steam to the medium-pressure system; a medium-pressure steam pipe that connects the medium-pressure system and a cooling system of the gas turbine and that supplies the medium-pressure steam from the medium-pressure system to the cooling system; and a steam supplying pipe that connects the high-pressure drum and the medium-pressure drum.

Abstract: A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged a circumferential direction on an external circumferential surface of the fuel nozzle, each of which extends along an axial direction of the fuel nozzle, and gradually curves from upstream to downstream so as to swirl air flowing in the air passage from the upstream to the downstream, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane surface of each of the swirler vanes, and a cooling unit that cools a part of the vane surface on which the liquid fuel hits. The cooling unit includes a water cooling circuit formed inside the swirler vane.

Abstract: A fuel system for an aircraft comprises a boost pump, a main fuel pump and a motive pump. The boost pump receives fuel from a storage unit. The main fuel pump receives fuel from the boost pump and delivers fuel to a distribution system. The motive fuel pump receives fuel from the boost pump, routes fuel through the storage unit, and delivers fuel to an actuator.

Abstract: A heat shield manifold system for an inner casing between a compressor and turbine assembly is disclosed. The heat shield manifold system protects the outer case from high temperature compressor discharge air, thereby enabling the outer case extending between a compressor and a turbine assembly to be formed from less expensive materials than otherwise would be required. In addition, the heat shield manifold system may be configured such that compressor bleed air is passed from the compressor into the heat shield manifold system without passing through a conventional flange to flange joint that is susceptible to leakage.

Abstract: Oil and fuel circuits in a turbine engine, the circuits including a main oil/fuel heat exchanger passing flows of oil and fuel for cooling the oil, an oil/air heat exchanger mounted in the oil circuit and having a flow of cooling air passing therethrough, a bypass pipe connected between an oil inlet and outlet of the oil/air heat exchanger, a valve for controlling passage of the oil flow through the bypass pipe and the oil/air heat exchanger, and a secondary oil/fuel heat exchanger mounted in the bypass pipe.

Abstract: An oscillating heat pipe of a gas turbine engine includes a plurality of channels that define a continuous loop through which a fluid flows, and an evaporator of a gas turbine engine. The fluid flows through the evaporator to accept heat from a first fluid. The first fluid is located near or in an engine core. The oscillating heat pipe also includes condenser of the gas turbine engine. The fluid flows through the condenser to reject heat to a second fluid, and the second fluid is located outwardly of the engine core.

Abstract: The invention is about a submerged combustion method and the device; specifically, it is a submerged combustion method and the device utilizing turbine heat engine principle. In the invention, turbine power combustion means is used and substitutes the conventional submerged combustion system that must equip air blowing means. The high temperature gases generated from the combustion within the turbine power combustion means will do work on the turbine, which will drive the air compressor means of the turbine power combustion means to induce air for combustion, and will drive the second-time complete combustion of high temperature gases and the complement fuel, and then the gases will come out from water bottom against tank water pressure and carry out heat interchange with tank water. The turbine submerged combustion boiler device of the invention need not equip air blowing means which would consume additional energy. Thus, it has high energy efficiency and a simple system structure.

Abstract: A method of heating liquid fuel upstream of a combustor in a system where compressor discharge air is cooled before being supplied to fuel nozzles in the combustor includes the steps of passing the compressor discharge air through a heat exchanger in heat exchange relationship with the liquid fuel to heat the liquid fuel and cool the compressor discharge air; supplying the heated liquid fuel and the cooled compressor discharge air to the combustor.

Abstract: An axial-flow turbine has turbine nozzles, a heat shield plate, a first communication hole formed in the turbine rotor and connected to the space, to flow a cooling medium, a first opening formed in at least any one of the two adjacent rotor disks, to be connected to the space, a second communication hole connected to the space through the first opening, to communicate with an implant unit of the turbine rotor blade in the rotor disk, a third communication hole connected to the second communication hole, to communicate along an effective length of the turbine rotor blade, a second opening formed in a side face of the turbine rotor blade, to be connected to the third communication hole, and a third opening formed in an outer circumferential end face of the turbine rotor blade, to be connected to the third communication hole.

Abstract: Setting in place of one or several coolers in the wall of a secondary flow of a bypass turbomachine. The wall extends from an intermediate casing toward a leading edge of a separator nose between a primary flow and the secondary flow. The wall includes a series of support arms attached to an intermediate casing, distributed over the perimeter of the wall and directed upstream. A series of surface air-oil heat exchangers forming wall segments are arranged end-to-end on the support arms, so as to form an annular wall. A shroud having a leading edge is arranged and fixed in the area of the upstream edges of the heat exchangers, so as to complete the wall. The support arms include hydraulic connectors connected to one another on each arm, adapted to cooperate with corresponding connectors in the area of the heat exchangers and in the area of the intermediate casing.

Abstract: An oil cooler is provided for a wall of an air flow passage of a gas turbine engine. The oil cooler has a heat exchanger with an oil conduit for carrying a flow of heated oil proximal to the wall of the air flow passage. The heat exchanger is arranged to transfer heat from the heated oil to the air flowing through the passage. The oil cooler further has a system for altering the flow of air across the heat exchanger such that the heat transfer effectiveness of the heat exchanger can be adjusted.

Abstract: A method and apparatus are disclosed which are directed generally to gas turbine engine systems and specifically to a method utilizing a heat pipe or pipes associated with a thermal oxidizer for preheating a fuel-air mixture. This preheating of a fuel-air mixture allows a substantial reduction in size a thermal oxidizer used as a combustor so that it can be used with all fuels, especially natural gas.

Abstract: Methods for optimizing a thermocline in a thermal energy storage fluid within a thermal energy storage tank are disclosed. The methods comprise identifying a thermocline region in the fluid, adding thermal energy to a fluid stream extracted from the thermocline region, and returning the fluid stream to the tank at a plurality of locations above the thermocline region. The methods further comprise regulating the temperature of the fluid returned to the tank at a set point temperature by modulating the flow rate of the fluid stream and by changing the location from where the fluid is extracted from the tank.

Abstract: An aircraft adaptive power thermal management system for cooling one or more aircraft components includes an air cycle system, a vapor cycle system, and a fuel recirculation loop operably disposed therebetween. An air cycle system heat exchanger is between the air cycle system and the fuel recirculation loop, a vapor cycle system heat exchanger is between the vapor cycle system and the fuel recirculation loop, and one or more aircraft fuel tanks are in the fuel recirculation loop. An intercooler including a duct heat exchanger in an aircraft gas turbine engine FLADE duct may be in the air cycle system. The system is operable for providing on-demand cooling for one or more of the aircraft components by increasing heat sink capacity of the fuel tanks.

Abstract: A method of assembling a heat exchanger in a gas turbine engine assembly is provided. The method includes providing a structural body including a wall having an elongated slot, providing a heat exchanger operably associated with a bracket, and providing a slip joint for coupling the bracket to the structural body. The slip joint includes a standoff, an elongated member, and a biasing member disposed about the elongated member. The standoff is inserted through the wall so that the biasing member imparts a predetermined biasing force between the bracket and the structural body. The slip joint allows relative sliding movement between the bracket and the structural body when a sliding force due to thermal expansion or contraction is greater than the biasing force.

Abstract: A gas turbine includes a compressor, a combustor downstream from the compressor and a heat transfer system, wherein the heat transfer system receives a compressed working fluid from the compressor. A fluid coupling between the heat transfer system and the combustor, wherein the fluid coupling receives the compressed working fluid from the heat transfer system. A conditioner in fluid communication with the compressor and a fluid coupling between the heat transfer system and the conditioner, wherein the fluid coupling receives a cooling media from the heat transfer system. A method for operating the gas turbine includes flowing a compressed working fluid from the compressor to the heat transfer system, transferring heat energy from the compressed working fluid to the heat transfer system, flowing the compressed working fluid from the heat transfer system to a combustor, and flowing a cooling media from the heat transfer system to a compressor inlet.

Abstract: A cooling system for electronics in a gas turbine engine system comprises an electronic device cooled by a fluid recirculation loop. The fluid recirculation loop comprises a fluid line to carry coolant fluid, a heat pump on the fluid line for removing heat from the coolant fluid, and a fluid pump on the fluid line to circulate the coolant fluid through the loop. The electronic device is in thermal communication with the fluid circulation loop.

Abstract: A system for cooling one or more circulating flows of oil, the system including: one or more fuel-oil heat exchangers, the fuel-oil heat exchangers using fuel for an engine to cool at least one of one or more circulating flows of oil; and a fuel return line in flow communication with a point downstream of the fuel-oil heat exchangers and a point upstream of the fuel-oil heat exchangers, wherein the fuel return line is arranged so that at least a portion of the fuel exiting the fuel-oil heat exchangers may be diverted to the point upstream of the fuel-oil heat exchangers. Furthermore, a system for cooling a circulating flow of oil may include one or more fuel-oil heat exchangers and one or more air-fuel heat exchangers, the fuel-oil heat exchangers using fuel to cool the circulating flow of oil and the air-fuel heat exchangers using air to cool the fuel.

Abstract: According to the invention, in order to prevent a film from forming which obstructs the transfer of heat in heat exchanger pipes, the heat exchanger pipe comprises an external side which is adjacent to the external surface and which is impinged upon by a steam medium, and an inner side which is adjacent to an inner surface and which is impinged upon by a coolant, such that the outer surface is provided with a first layer which reduces the adhesion of the steam on the outer surface and/or the inner surface is provided with a second layer which reduces the adhesion of a coolant to the inner surface and which is embodied as a biocidal layer. The invention relates to a heat exchanger and to the use thereof.

Abstract: In one embodiment a gas turbine engine is disclosed having a heat exchanger at least partially disposed in a bypass duct. In one form the gas turbine engine is a high bypass ratio engine. The heat exchanger may be coupled with a directed energy weapon to provide coolant flow and regulate the temperature of the directed energy weapon. Other devices may also be coupled with the heat exchanger, either as an alternative to in addition to the directed energy weapon.

Abstract: A gas turbine engine is provided with a first heat exchanger associated with a cooling air flow to deliver cooling air to a turbine section. A second heat exchanger is associated with a fuel supply line for delivering fuel into a combustion section. An intermediate fluid cools air at the first heat exchanger and heats fuel at the second heat exchanger.

Abstract: An injection nozzle for a turbomachine includes a main body having a first end portion that extends to a second end portion defining an exterior wall having an outer surface. A plurality of fluid delivery tubes extend through the main body. Each of the plurality of fluid delivery tubes includes a first fluid inlet for receiving a first fluid, a second fluid inlet for receiving a second fluid and an outlet. The injection nozzle further includes a coolant delivery system arranged within the main body. The coolant delivery system guides a coolant along at least one of a portion of the exterior wall and around the plurality of fluid delivery tubes.

Abstract: A burner comprising channels for the separate supply of a liquid fuel and an oxygen-containing gas. The burner comprises a twin-fluid atomizer head comprising first flow-through passages fluidly connected to the supply channel for oxygen-containing gas and second flow-through passages fluidly connected to the fuel supply channel. The second flow-through passages exit into the first flow-through passages at a point before the first flow-through passages exit into a coaxial ring of orifices. A cooling jacket envelopes the supply channel walls. The orifices run through the atomizer head at a distance from the cooling jacket. The atomizer head can, for example, be made of a first metal, such as a copper alloy, and the cooling jacket can be made of a second metal with a lower thermal conductivity than the first metal, for example steel.

Abstract: The invention relates to a gas turbine combustion chamber with a combustion chamber wall 1, with at least part of the combustion chamber wall 1 being provided with a liquid-cooling system.

Abstract: An air intake system for a gas turbine includes one or more coils in airflow communication with an inlet arrangement. Each coil is constructed and arranged to have a respective upstream face velocity that is intended to be within 20% of the other coils. Each coil utilizes a working fluid of a predetermined temperature range conveyed there through and a plurality of spaced fins. The fins are spaced apart to permit air to flow between adjacent fins as air flows through the coil. At least one of the coils has a number of fins per inch that is different from the number of fins per inch of the other coils. Alternatively, each individual coil has at least one section with fewer or greater numbers of fins per inch that the other sections of that coil.

Abstract: A cooling system for a high-speed vehicle may comprise a combustor wall at least partially enclosing a combustor and which is cooled using a coolant circulating in a Brayton cycle. The heated coolant may be expanded in a turbine, transfer heat to a fuel within a heat exchanger, and be compressed by a compressor before returning to the combustor wall. The combustor wall may be capable of withstanding high temperatures, higher than the temperature at which fuel coking may take place. Heat transfer takes place between the coolant and the combustor wall, and between the coolant and the fuel. A method of cooling an engine for a high-speed vehicle is also disclosed.

Abstract: A power generation system and method in which a fuel gas is introduced into a combustor and at least a portion of the fuel gas is combusted in the combustor, producing an exhaust gas having no appreciable available oxygen. The exhaust gas is introduced as a working fluid into a gas turbine, thereby generating power. Cooling of the power generation system is accomplished using a cooling fluid selected from the group consisting of synthesis gas, natural gas, natural gas/steam mixture, flue gas, flue gas/steam mixture, and mixtures thereof.

Abstract: A fuel injector in a combustor apparatus of a gas turbine engine. An outer wall of the injector defines an interior volume in which an intermediate wall is disposed. A first gap is formed between the outer wall and the intermediate wall. The intermediate wall defines an internal volume in which an inner wall is disposed. A second gap is formed between the intermediate wall and the inner wall. The second gap receives cooling fluid that cools the injector. The cooling fluid provides convective cooling to the intermediate wall as it flows within the second gap. The cooling fluid also flows through apertures in the intermediate wall into the first gap where it provides impingement cooling to the outer wall and provides convective cooling to the outer wall. The inner wall defines a passageway that delivers fuel into a liner downstream from a main combustion zone.

Abstract: Heat exchanger systems and associated systems and methods for cooling aircraft starters/generators are disclosed. A system in accordance with one embodiment includes a first fluid flow path for a first fluid, a second fluid flow path for a second fluid, and a third fluid flow path for a third fluid. The first and second flow paths are positioned proximate to the third flow path to transfer heat between the third fluid and both the first and second fluids. The third flow path is configured to allow a transfer of heat between the second and third fluids at a first transfer rate when the first fluid carries heat at a first rate, and at a second transfer rate different than the first transfer rate when the first fluid does not carry heat, or carries heat at a second rate less than the first rate. Accordingly, when the heat to be rejected by one fluid is decreased, the heat transfer rate for the remaining fluid can be increased.