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公开(公告)号：US12123351B2
公开(公告)日：2024-10-22
申请号：US17484897
申请日：2021-09-24
申请人： ROLLS-ROYCE plc
CPC分类号： F02C7/18 , F01D25/12 , F02C7/04 , F02C7/143 , F02C7/185 , F02K3/065 , F05D2260/213 , F05D2260/232 , F05D2260/36 , F05D2260/606
摘要： A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D), and the heat exchanger module comprises a plurality of heat exchanger elements. The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, with the heat exchanger module having an axial length along a central axis between an upstream-most face of the heat exchanger elements and a downstream-most face of the heat exchanger elements. The axial length is in the range of 0.1*D to 5.0*D.
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2.发明公开公开(公告)号：US20240200491A1
公开(公告)日：2024-06-20
申请号：US18407648
申请日：2024-01-09
申请人： RTX CORPORATION
发明人： Edward Thomas Rocco , Danbing Seto , Coy Bruce Wood , Liang Tang
CPC分类号： F02C3/30 , F02C3/22 , F02C7/185 , F05D2220/323 , F05D2260/211 , F05D2260/213 , F05D2260/2322 , F05D2260/607 , F05D2260/80 , F05D2270/3015
摘要： A propulsion system for an aircraft includes a hydrogen fuel system, a water recovery system and a water pressure and quantity monitoring system. The water recovery system uses a condenser to extract water from an exhaust gas flow. The water pressure and quantity monitoring system measures water pressures and quantities at various locations in the water recovery system to assess the health and efficiency of the water recovery/supply system and the propulsion system.
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公开(公告)号：US11920517B2
公开(公告)日：2024-03-05
申请号：US17872355
申请日：2022-07-25
CPC分类号： F02C7/185 , F02C7/18 , F02K3/115 , F05D2260/213
摘要： A turbine engine heat exchanger has an array of heat exchanger plates mounted to an inner case wall for providing heat transfer from a bleed flowpath to a bypass flowpath. Each plate has: first and second faces along the bypass flowpath; a proximal edge mounted to the inner case wall; an inlet along the proximal edge; an outlet along the proximal edge; and a branch segment of the bleed flowpath passing from the inlet to the outlet.
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公开(公告)号：US11846422B2
公开(公告)日：2023-12-19
申请号：US17406767
申请日：2021-08-19
申请人： Delavan Inc.
IPC分类号： F23R3/28 , F02C7/18 , F02C7/224 , F02C9/18 , F23R3/26 , F02C6/08 , F02C7/141 , F02C7/22 , F02C9/16
CPC分类号： F23R3/283 , F02C7/185 , F02C7/224 , F02C9/18 , F23R3/26 , F02C6/08 , F02C7/141 , F02C7/222 , F02C9/16 , F05D2260/213 , F05D2260/232 , F05D2270/303
摘要： A system includes an air manifold, a fuel manifold, and a plurality of fuel injectors. At least one of the fuel injectors includes a heat exchanger portion for supplying compressed, cooled air form the heat exchanger portion to the air manifold. An air valve is operatively connected to an outlet of the air manifold for controlling release of air from the air manifold. A controller is operatively connected to the air valve, wherein the controller includes machine readable instructions configured to control the air valve to regulate flow of air through the air valve based on fuel temperatures in the fuel channel. The machine readable instructions can be configured to cause the controller to flow air through the air valve in a heat exchange mode if a fuel temperature in the fuel injectors is below a predetermined fuel temperature.
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公开(公告)号：US20230332510A1
公开(公告)日：2023-10-19
申请号：US17719379
申请日：2022-04-13
CPC分类号： F01D21/003 , F01D17/085 , F02C9/28 , F02C7/141 , F02C7/185 , F05D2260/606 , F05D2260/83 , F05D2220/323 , F05D2260/213 , F05D2260/80
摘要： A method of transient control of a thermal transport bus of a turbomachine includes measuring a measured temperature and a measured pressure of a working fluid; determining a selected run state of a turbomachine, wherein the selected run state is one of a plurality of run states; selecting a desired operating condition comprising a desired temperature range and a desired pressure range as a function of a desired state of the working fluid; comparing the measured temperature with the desired temperature range, and comparing the measured pressure with the desired pressure range; and modulating control of the thermal transport bus as a function of the comparing of the measured temperature with the desired temperature range and the comparing of the measured pressure with the desired pressure range.
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公开(公告)号：US11788472B2
公开(公告)日：2023-10-17
申请号：US17479502
申请日：2021-09-20
申请人： RTX Corporation
发明人： Steven W. Burd
CPC分类号： F02C7/36 , F02C7/185 , F02C7/32 , F05D2220/323 , F05D2220/76
摘要： Aircraft generator systems are described. The aircraft generator systems include a main engine having a fan and a compressor section, a generator assembly having at least one expansion turbine operably connected to a generator, and a working fluid flow path defined between at least one extraction point at at least one of the fan and the compressor section of the main engine and at least one outlet, wherein the working fluid is configured to flow through the at least one expansion turbine to generate power at the generator. There are no heat exchangers arranged between the at least one extraction point and the at least one outlet along the working fluid flow path.
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公开(公告)号：US11788470B2
公开(公告)日：2023-10-17
申请号：US17188668
申请日：2021-03-01
发明人： Jeffrey Douglas Rambo , Brandon Wayne Miller , Kevin Robert Feldmann , Patrick Michael Marrinan , Robert Jon McQuiston
CPC分类号： F02C7/185 , F01D25/12 , F02C7/14 , F05D2220/323 , F05D2260/20 , F05D2270/112 , F05D2270/301 , F05D2270/3032
摘要： A method is provided of controlling a cooled cooling air system for an aeronautical gas turbine engine. The method includes: receiving data indicative of an ambient condition of the aeronautical gas turbine engine, data indicative of a deterioration parameter of the aeronautical gas turbine engine, data indicative of an operating condition of the aeronautical gas turbine engine, or a combination thereof; and modifying a cooling capacity of the cooled cooling air system in response to the received data indicative of the ambient condition of the aeronautical gas turbine engine, data indicative of the deterioration parameter of the aeronautical gas turbine engine, data indicative of an operating condition of the aeronautical gas turbine engine, or the combination thereof.
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公开(公告)号：US11753995B1
公开(公告)日：2023-09-12
申请号：US17730570
申请日：2022-04-27
CPC分类号： F02C7/224 , F02C3/22 , F02C7/143 , F02C7/185 , F02C9/40 , F05D2220/323 , F05D2260/211 , F05D2260/213
摘要： A turbofan engine includes a fan, a core turbine engine having one or more turbines and an exhaust section, and a hydrogen-exhaust gas heat exchanger in flow communication with the exhaust section and hydrogen flowing along a hydrogen supply line. The hydrogen-exhaust gas heat exchanger defines a load capacity factor determined by raising a product to a one-quarter power, the product being determined by multiplying a heat transfer surface area density associated with the hydrogen-exhaust gas heat exchanger by a process conductance parameter that relates characteristics of hydrogen, ambient air, and exhaust gas at takeoff, as well as a fan diameter of the fan and a number of turbine stages of the turbofan engine. The load capacity factor is between 4.37 and 28.65 for the fan diameter being between 0.5 and 3.5 meters and the heat transfer surface area density being between 500 m2/m3 and 10,000 m2/m3.
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公开(公告)号：US11686249B2
公开(公告)日：2023-06-27
申请号：US16970815
申请日：2019-02-18
CPC分类号： F02C7/143 , F01D9/065 , F02C6/08 , F02C7/14 , F02C7/185 , F02K3/115 , F02C7/047 , F05D2220/323 , F05D2260/213 , F05D2260/98
摘要： An aircraft turbine engine having a primary air flow path with low-pressure and high-pressure compressors, a secondary air flow path which is located around the primary path and runs coaxially thereto, the turbine engine including vanes distributed about a main axis of the turbine engine. A pressurized air circuit draws air between the low-pressure compressor and the high-pressure compressor or in the high-pressure compressor and supplies at least one component located close to a main axis of the turbine engine. The pressurized air circuit includes a heat exchanger between the stream of pressurized air and the stream of air flowing in the secondary path, the heat exchanger being arranged in at least one of the straightening vanes, where a heat exchanger pipe is arranged, the pipe having a pressurized-air inlet and a pressurized-air outlet that are located at the same radial end of the vane.
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公开(公告)号：US20230193833A1
公开(公告)日：2023-06-22
申请号：US17554853
申请日：2021-12-17
CPC分类号： F02C9/18 , F02C7/185 , F02C6/08 , F05D2220/50 , F05D2260/232 , F05D2260/213 , F05D2260/601 , F05D2260/606 , F05D2270/3011 , F05D2270/3015
摘要： A bleed air control system is configured to vary the air pressure at the inlet of a gas turbine engine. The bleed air control system includes a first gas turbine engine configured to provide bleed air, a second gas turbine engine acting as an auxiliary power unit, and a bleed air control system configured to selectively provide bleed air from the first gas turbine engine to the second gas turbine engine.
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