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公开(公告)号：US20240360788A1
公开(公告)日：2024-10-31
申请号：US18771005
申请日：2024-07-12
申请人： RTX CORPORATION
CPC分类号： F02C3/30 , F02C1/10 , F02C3/22 , F02C6/18 , F02C7/141 , F05D2220/323 , F05D2260/213
摘要： An aircraft propulsion system includes a core engine and a bottoming cycle where a working fluid is circulated within a closed circuit. A first heat exchanger is used to transfer heat from a portion of thermal energy from the exhaust gas flow to working fluid of the bottoming cycle. A fuel/working fluid heat exchanger provides the cryogenic fuel to cool the working fluid exhausted from a bottoming turbine and before a bottoming compressor.
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公开(公告)号：US20240360771A1
公开(公告)日：2024-10-31
申请号：US18308968
申请日：2023-04-28
发明人： Michael G. McCaffrey
CPC分类号： F01D11/14 , F02C7/28 , F05D2240/55
摘要： A blade outer airseal (BOAS) assembly of a gas turbine engine includes a plurality of BOAS segments arrayed circumferentially about the engine central longitudinal axis, and a plurality of BOAS carriers located radially outboard of the plurality of BOAS segments. Each BOAS carrier is supportive of at least one BOAS segment. The BOAS assembly includes plurality of adjustment levers. Each adjustment lever is operably connected to at least two BOAS carriers of the plurality of BOAS carriers. Rotation of each adjustment lever about a respective pivot axis urges movement of the plurality of BOAS segments in a radial direction thereby adjusting a radial gap between the turbine rotor and the plurality of BOAS segments.
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3.发明授权公开(公告)号：US12129813B1
公开(公告)日：2024-10-29
申请号：US18633815
申请日：2024-04-12
CPC分类号： F02K7/10 , F02C1/08 , F02C1/10 , F04D21/00 , F05D2220/10 , F05D2220/76
摘要： A new power plant cycle facilitated by an innovative vapor compression apparatus to repressurize the air vapor and generate renewable energy for heat input to the cycle. The new cycle can be used in place of the conventional low efficiency Rankine cycle or other cycles to provide economical production of electricity without air pollution. The new cycle can also be used on-board land-based vehicles, aircraft, and watercraft to power them electrically or mechanically, or be used in a package unit for supplying electricity and controlling temperatures of indoor homes, business, and other structures. The new cycle can be used in Ramjet aircraft applications.
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公开(公告)号：US12129796B1
公开(公告)日：2024-10-29
申请号：US18138366
申请日：2023-04-24
CPC分类号： F02C7/057 , F01D25/08 , F05D2240/127
摘要： A vortex restart structure including a flow passage having a first wall and a second wall opposite the first wall, each of the first wall and the second wall including a parting surface; multiple flow turbulators extending from at least one parting surface of the first wall or the second wall; and at least one vortex restart structure extending from at least one parting surface of the first wall or the second wall, wherein the at least one vortex restart structure extends from the parting surface into the flow passage beyond the multiple flow turbulators.
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公开(公告)号：US12129795B2
公开(公告)日：2024-10-29
申请号：US17598987
申请日：2020-03-19
CPC分类号： F02C7/057 , B64D33/02 , F02C7/042 , F05D2260/50
摘要： An air inlet duct or a nacelle of an aircraft propulsion assembly includes an annular body and an annular air inlet lip with two coaxial annular walls, inner and outer, respectively. The inner wall defining a portion of an inner annular surface of the air inlet duct and the outer wall defining a portion of an outer annular surface of the air inlet duct. A control system translates the lip from a first position, in which the lip is attached to the body, to a second position, in which the lip is axially separated from the body. An annular row of grilles is translatably secured to the lip. The grilles are housed inside the body in the first position and extended from the body in order for an air flow entering the air inlet duct to pass therethrough in the second position.
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公开(公告)号：US20240356314A1
公开(公告)日：2024-10-24
申请号：US18759692
申请日：2024-06-28
IPC分类号： H02B7/06 , E21B41/00 , E21B43/26 , F02C3/22 , F04B17/03 , F04B23/04 , F04B35/04 , F04B47/02 , F04B49/20
CPC分类号： H02B7/06 , E21B41/00 , E21B43/26 , F02C3/22 , F04B17/03 , F04B23/04 , F04B35/04 , F04B47/02 , F04B49/20
摘要： A hydraulic fracturing system for fracturing a subterranean formation is disclosed. In an embodiment, the system may include a plurality of electric pumps fluidly connected to a well associated with the subterranean formation and powered by at least one electric motor, and configured to pump fluid into a wellbore associated with the well at a high pressure so that the fluid passes from the wellbore into the subterranean formation and fractures the subterranean formation; at least one generator electrically coupled to the plurality of electric pumps so as to generate electricity for use by the plurality of electric pumps; and at least one switchgear electrically coupled to the at least one generator and configured to distribute an electrical load between the plurality of electric pumps and the at least one generator.
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公开(公告)号：US20240352942A1
公开(公告)日：2024-10-24
申请号：US18762512
申请日：2024-07-02
申请人： RTX CORPORATION
CPC分类号： F04D29/324 , F01D5/142 , F01D5/146 , F01D5/3007 , F01D5/3038 , F01D5/34 , F04D19/02 , F04D29/321 , F04D29/322 , F04D29/644 , F01D9/041 , F02C3/04 , F05D2220/32
摘要： A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade.
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公开(公告)号：US20240352890A1
公开(公告)日：2024-10-24
申请号：US18302963
申请日：2023-04-19
发明人： Dave MENHEERE
IPC分类号： F02C7/06 , F04B1/0465 , F04B1/1071 , F16N13/02
CPC分类号： F02C7/06 , F04B1/0465 , F04B1/1071 , F16N13/02 , F04B1/0408 , F04B1/0421 , F04B1/0439
摘要： The pump can have a support having a guide extending around an axis, a radial position of the guide relative the axis varying around the axis, and a first oil passage formed in the support; a rotary assembly mounted to the support via support bearings, and rotatable around the axis, the rotary assembly having a second oil passage and a cylinder, the cylinder extending radially relative the axis, an inlet port fluidly connecting the first oil passage to the cylinder, and an outlet port fluidly connecting the cylinder to the second oil passage, and a piston slidingly mounted in the cylinder, a radially-outer end of the piston further slidingly engaged with the guide.
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公开(公告)号：US20240352888A1
公开(公告)日：2024-10-24
申请号：US18138366
申请日：2023-04-24
CPC分类号： F02C7/057 , F01D25/08 , F05D2240/127
摘要： A vortex restart structure including a flow passage having a first wall and a second wall opposite the first wall, each of the first wall and the second wall including a parting surface; multiple flow turbulators extending from at least one parting surface of the first wall or the second wall; and at least one vortex restart structure extending from at least one parting surface of the first wall or the second wall, wherein the at least one vortex restart structure extends from the parting surface into the flow passage beyond the multiple flow turbulators.
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公开(公告)号：US20240352872A1
公开(公告)日：2024-10-24
申请号：US18304037
申请日：2023-04-20
摘要： An example system includes one or more heaters configured and positioned to add thermal energy to one or more portions of a gas turbine engine after the gas turbine engine was in operation, wherein the thermal energy minimizes or prevents undesired contact or seizing of a rotor of the gas turbine engine with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation. The system further includes a controller configured to control operation of the one or more heaters.
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