公开(公告)号：US12203415B2

公开(公告)日：2025-01-21

申请号：US18337678

申请日：2023-06-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： John Sgouromitis ,  Kashif Mohammed ,  Sylvain Lamarre

IPC: F02C7/18 ,  F01D21/14 ,  F02K3/115

Abstract: An aircraft engine comprises an exhaust duct receiving an engine gas flow at a first pressure during an operating condition and at a second, lower pressure at shutdown. A heat exchanger duct connected to the exhaust duct has a heat exchanger disposed therein. A cover in the heat exchanger duct includes a closure movable between open and closed positions to fluidly connect or disconnect the heat exchanger duct to the exhaust duct. A biasing member disposed in the exhaust duct, exposed to the gas flow, and operatively connected to the closure biases the closure toward the closed position with a biasing force. First and second forces opposing the biasing force are generated on the biasing member by the gas flow at the first and second pressures, the first being greater than the second. The biasing force is greater than the second force and less than the first force.

公开(公告)号：US12188433B2

公开(公告)日：2025-01-07

申请号：US18539813

申请日：2023-12-14

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M Hussain ,  Vasileios Kyritsis

IPC: F02C7/18 ,  F02K3/115

Abstract: A thermal management system for a gas turbine engine includes a plurality of inlet and outlet vanes extending from a bypass inner wall towards an outer cowl, a plurality of first removable shims, a plurality of second removable shims, and a third removable shim. Each first removable shim extends between and engages the outer cowl and a corresponding inlet vane. Each second removable shim extends between and engages the outer cowl and a corresponding outlet vane. The third removable shim extends between and engages a heat exchanger and the outer cowl. Each of the plurality of first removable shims, each of the plurality of second removable shims, and the third removable shim is removable for positionally adjusting the outer cowl relative to the bypass inner wall.

公开(公告)号：US20240068377A1

公开(公告)日：2024-02-29

申请号：US18261443

申请日：2022-01-07

Applicant: SAFRAN ,  SAFRAN AIRCRAFT ENGINES

Inventor： Thierry SIBILLI ,  Vincent François Georges MILLIER ,  Loïc Paul Yves GUILLOTEL

IPC: F01D15/10 ,  B64D27/24 ,  F02C7/12 ,  F02K3/115

CPC classification number: F01D15/10 ,  B64D27/24 ,  F02C7/12 ,  F02K3/115 ,  F02K3/06

Abstract: A hybrid turbofan engine for an aircraft, comprising a fan, an electric motor/generator and a gas generator, the engine comprising, between the fan and a splitter that separates the flows, an internal wall for delimiting an air duct, situated upstream of inlet guide vanes of a primary duct, and, upstream of outlet guide vanes, an internal upstream wall for delimiting a secondary duct, the motor/generator having a stator carried by a stator support fixed to a stator part of the engine. According to the invention, a plurality of heat pipe for cooling the motor/generator are provided, each heat pipe having an evaporation section fixed to the stator support, and a condensation section fixed to the internal wall or the internal upstream wall.

公开(公告)号：US11754021B2

公开(公告)日：2023-09-12

申请号：US17407880

申请日：2021-08-20

Applicant: Raytheon Technologies Corporation

Inventor： Amanda Jean Learned Boucher ,  Joseph B. Staubach

IPC: F02K3/115 ,  F02K3/06

CPC classification number: F02K3/115 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/606

Abstract: Aircraft propulsion systems including a closed loop-supercritical fluid system having a turbine, a cooler heat exchanger, a compressor, and a recovery heat exchanger arranged along a closed-loop flow path of a supercritical fluid. A shaft is operably coupled to the turbine and configured to be rotationally driven by the turbine. A fan is configured to generate thrust, the fan operably coupled to the shaft to be rotationally driven by the shaft. A burner is configured to combust a fuel and air from the fan to generate a combusted gas and supply said combusted gas to the recovery heat exchanger of the closed loop-supercritical fluid system and out an exhaust nozzle.

公开(公告)号：US20230056536A1

公开(公告)日：2023-02-23

申请号：US17407880

申请日：2021-08-20

Applicant: Raytheon Technologies Corporation

Inventor： Amanda Jean Learned Boucher ,  Joseph B. Staubach

IPC: F02K3/115 ,  F02K3/06

Abstract: Aircraft propulsion systems including a closed loop-supercritical fluid system having a turbine, a cooler heat exchanger, a compressor, and a recovery heat exchanger arranged along a closed-loop flow path of a supercritical fluid. A shaft is operably coupled to the turbine and configured to be rotationally driven by the turbine. A fan is configured to generate thrust, the fan operably coupled to the shaft to be rotationally driven by the shaft. A burner is configured to combust a fuel and air from the fan to generate a combusted gas and supply said combusted gas to the recovery heat exchanger of the closed loop-supercritical fluid system and out an exhaust nozzle.

公开(公告)号：US20220372914A1

公开(公告)日：2022-11-24

申请号：US17872355

申请日：2022-07-25

Applicant: Raytheon Technologies Corporation

Inventor： James F. Wiedenhoefer ,  Russell J. Bergman ,  William P. Stillman ,  Patrick M. Hart

IPC: F02C7/18 ,  F02K3/115

Abstract: 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

公开(公告)号：US11492977B2

公开(公告)日：2022-11-08

申请号：US16431955

申请日：2019-06-05

Applicant: United Technologies Corporation

Inventor： Nicholas W. Kantany ,  Edward Boucher ,  Kristine Marie Carnavos ,  Robert Russell Mayer ,  Donald W. Peters

IPC: F02C7/28 ,  F02C9/20 ,  F02K3/075 ,  F02K3/115

Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.

公开(公告)号：US11421598B2

公开(公告)日：2022-08-23

申请号：US16781424

申请日：2020-02-04

Applicant: United Technologies Corporation

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F28D1/053 ,  F28F13/06 ,  F28D1/04 ,  F28F13/08 ,  F02K3/115 ,  F02C7/14 ,  F28D21/00 ,  F28D1/02 ,  F02C3/04 ,  F02C7/36 ,  F02C9/18

Abstract: A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.

公开(公告)号：US11268443B2

公开(公告)日：2022-03-08

申请号：US16253352

申请日：2019-01-22

Applicant: Safran Nacelles

Inventor： Vincent Peyron ,  Patrick Gonidec ,  Jean-Nicolas Bouchout

IPC: F02C7/14 ,  F02C7/16 ,  F02K3/115 ,  B64D33/10 ,  F02C7/00 ,  B64D29/06 ,  B64D33/08 ,  F02K3/06

Abstract: A nacelle of a turbine engine has a substantially tubular structure and defines a secondary channel. The nacelle includes a shroud forming a trailing edge on a downstream end of the nacelle, the shroud being defined by at least one outer face subjected to an outside air flow and an inner face subjected to an inside air flow circulating in the secondary channel of the nacelle. The nacelle further includes a cooling device having at least one heat-exchange channel that extends into the shroud.

公开(公告)号：US11208954B2

公开(公告)日：2021-12-28

申请号：US16453061

申请日：2019-06-26

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

Inventor： James C. Loebig ,  Emil R. Dejulio

IPC: F02C7/18 ,  F28D9/00 ,  F02C7/143 ,  F28F3/04 ,  F28F9/02 ,  F28D21/00 ,  F02K3/115 ,  F02C3/04

Abstract: A microchannel heat exchanger (MCHX) includes an air-passage layer including a plurality of air-passage microchannels, a working fluid layer including a plurality of working fluid microchannels, and a sealing layer coupled to the working fluid layer to provide a working/sealing layer set. The working/sealing layer set includes an arrangement of raised pedestals. The raised pedestals may extend from the working fluid layer to the sealing layer and contact the sealing layer.