公开(公告)号：US11913405B2

公开(公告)日：2024-02-27

申请号：US18183232

申请日：2023-03-14

Applicant: Safran Aircraft Engines

Inventor： Fernando Gea Aguilera ,  Matthieu Fiack ,  Mathieu Simon Paul Gruber

IPC: F02K1/00 ,  F02K1/38 ,  F02C7/045 ,  F02C7/042 ,  F02K1/48 ,  F15D1/00

CPC classification number: F02K1/386 ,  F02C7/042 ,  F02C7/045 ,  F02K1/48 ,  F05D2220/323 ,  F05D2250/183 ,  F05D2250/61 ,  F05D2260/96 ,  F15D1/004 ,  F15D1/0035

Abstract: An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile having a succession of teeth and depressions. Along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.

公开(公告)号：US11885232B2

公开(公告)日：2024-01-30

申请号：US17624965

申请日：2020-02-13

Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.

Inventor： Yuichi Nakatani ,  Yuki Morisaki ,  Yasuhiro Saiki

IPC: F01D25/30 ,  B64D27/24 ,  F01D15/10 ,  F02C6/00 ,  F02K1/34 ,  F02K1/38

CPC classification number: F01D25/30 ,  B64D27/24 ,  B64D33/06 ,  F01D15/10 ,  F02C6/00 ,  F02K1/34 ,  F02K1/386 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2240/35

Abstract: A gas turbine system includes: a compressor configured to compress external air to generate compressed air; a combustor configured to burn the compressed air together with fuel to generate a combustion gas; a turbine configured to be driven by the combustion gas; an exhaust unit configured to guide the combustion gas, which has passed through the turbine, to outside; a shell having a cylindrical shape and extending along an axis line about which the turbine is configured to rotate and being arranged so as to cover the compressor, the combustor, the turbine, and the exhaust unit; and an exit unit configured to guide the combustion gas, which has passed through the turbine, to a discharge port in the surface of the shell.

公开(公告)号：US11754018B2

公开(公告)日：2023-09-12

申请号：US17554695

申请日：2021-12-17

Applicant: Rohr, Inc.

Inventor： Timothy Gormley

IPC: F02K1/12 ,  F02K1/36 ,  F02K1/38 ,  F02K1/46 ,  F02K1/15

CPC classification number: F02K1/1215 ,  F02K1/123 ,  F02K1/36 ,  F02K1/38 ,  F02K1/46 ,  F02K1/15 ,  F05D2250/323 ,  F05D2250/324 ,  F05D2260/56

Abstract: An apparatus is provided for an aircraft propulsion system. This apparatus includes an exhaust nozzle. The exhaust nozzle includes a flowpath, a passage, an outer door, an inner door and an actuator configured to move the outer door and the inner door between an open arrangement and a closed arrangement. The flowpath extends axially along a centerline through the exhaust nozzle. The passage extends laterally into the exhaust nozzle to the flowpath when the outer door and the inner door are in the open arrangement. The outer door is configured to pivot inwards towards the centerline when the outer door moves from the closed arrangement to the open arrangement. The inner door is configured to pivot outwards away from the centerline when the inner door moves from the closed arrangement to the open arrangement.

公开(公告)号：US11746726B2

公开(公告)日：2023-09-05

申请号：US17307570

申请日：2021-05-04

Applicant: Rohr, Inc.

Inventor： Adam Saunders ,  Bryce T. Kelford ,  Travis M. Frazier ,  Richard Haslim ,  Richard S. Alloway ,  Vijay V. Pujar

IPC: F02K1/52 ,  B64D29/06 ,  F02K1/80 ,  F02K1/04 ,  F02K1/82 ,  F02K1/38 ,  B64D27/26 ,  B64D27/18 ,  F02K3/06

CPC classification number: F02K1/52 ,  B64D27/18 ,  B64D29/06 ,  F02K1/805 ,  F02K3/06 ,  B64D27/26 ,  F05D2220/323 ,  F05D2240/128

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a nozzle extending axially along and circumferentially about an axial centerline. The nozzle includes a nozzle panel and a nozzle fairing fixedly connected to the nozzle panel at an axial end of the nozzle. The nozzle is configured with an internal flow passage radially between the nozzle panel and the nozzle fairing. The internal flow passage extends axially within the nozzle to an outlet between the nozzle panel and the nozzle fairing at the axial end of the nozzle.

公开(公告)号：US11506143B2

公开(公告)日：2022-11-22

申请号：US16477063

申请日：2018-01-11

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Remy Olivier Pargny ,  Alain Paul Madec

IPC: F02K1/48 ,  F02K1/38

Abstract: The invention relates to a concentric gas flow mixer in a multiple-flow turbomachine, comprising a nominally cylindrical upstream part and a downstream part having outer and inner lobes distributed peripherally around the tower of said mixer, characterised in that it comprises at least one modified lobe having a wall thickness, in at least one area, which is different from the other lobes, so as to modify the vibratory response of said mixer.

公开(公告)号：US11085398B2

公开(公告)日：2021-08-10

申请号：US16351031

申请日：2019-03-12

Applicant: Rohr, Inc.

Inventor： Michael Aten ,  Adam Saunders ,  Gary E. Bowman

IPC: F02K1/82 ,  F02K1/38 ,  F02K1/64 ,  F02K1/76 ,  F02K1/34

Abstract: A exhaust nozzle assembly comprises a nozzle that extends about an axial centerline and includes an exhaust nozzle flange; an radially inner surface that comprises an axially forward inner surface; a noise attenuating structure; a through hole inlet formed in the axially forward inner surface; a through hole outlet formed in the axially rear inner surface. The nozzle assembly also includes a radially outer surface that is radially separated from the radially inner surface by a nozzle cavity, where engine core air enters the nozzle cavity from the through hole inlet and exits the nozzle cavity axially downstream of the hole inlet via the through hole outlet.

公开(公告)号：US11053890B2

公开(公告)日：2021-07-06

申请号：US15580496

申请日：2016-06-10

Applicant: Safran Aircraft Engines

Inventor： Mario Cesar De Sousa ,  Benoit Argemiro Matthieu Debray ,  Dominique Michel Fouquet ,  Gregory Ghosarossian-Prillieux ,  Frederic Noel

IPC: F02K1/80 ,  F02K1/04 ,  F02K1/48 ,  F01D25/16 ,  F01D25/24 ,  F02K1/38

Abstract: The invention relates to an assembly comprising: a turbomachine exhaust case (110) that includes an external sleeve and an internal sleeve inside the former, both sleeves extending concentrically about a turbomachine axis, and also includes a plurality of arms extending radially between the sleeves; and an annular part (130) that is centered about the axis, is mounted on one sleeve of the exhaust case, and is located downstream of the exhaust case in the direction in which the air flows inside the turbomachine; the assembly is characterized in that the annular part and the sleeve of the exhaust case on which the annular part is mounted each have a circumferential thread (131, 115), said threads cooperating with each other in order to allow the annular part to be screwed onto the sleeve of the exhaust case.

公开(公告)号：US10954834B2

公开(公告)日：2021-03-23

申请号：US16057300

申请日：2018-08-07

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Yoonshik Shin ,  Yogendra Yogi Sheoran ,  Daniel Brown

IPC: F01N1/08 ,  F01D25/30 ,  F02K1/38 ,  F01N3/05 ,  F02C7/14

Abstract: Systems and methods for an exhaust system for a gas turbine engine are provided. The method includes: receiving a primary exhaust fluid in a primary manifold; receiving a secondary cooling fluid in a secondary plenum; directing the primary exhaust fluid through a plurality of eductor primary flow paths associated with a respective plurality of ducts spaced circumferentially about a primary manifold, the plurality of eductor primary flow paths extending through the secondary plenum; and mixing the primary exhaust fluid and the secondary cooling fluid in a mixing chamber associated with a respective one of the plurality of ducts to create a mixed fluid flow.

公开(公告)号：US10927791B2

公开(公告)日：2021-02-23

申请号：US16359152

申请日：2019-03-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Andre Julien ,  Jean Thomassin ,  Maxime Courtois ,  Bruno Villeneuve ,  Richard Ullyott ,  Serge Dussault ,  Luc Dionne ,  Serge Lafortune ,  Anthony Jones ,  Behzad Hagshenas ,  David H. Menheere

IPC: F02K1/38 ,  B64D41/00 ,  F01C1/22 ,  F02K5/00 ,  F02C5/00 ,  F02C7/14 ,  F02C7/18 ,  F02B63/04 ,  F02B63/06 ,  F02B67/04 ,  F01C21/18 ,  F01N3/05 ,  F01P5/02 ,  F01P11/10 ,  F02B53/02 ,  F02K1/82 ,  F02B53/00

Abstract: An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.

公开(公告)号：US20200378339A9

公开(公告)日：2020-12-03

申请号：US16105159

申请日：2018-08-20

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Guillaume BODARD ,  Jeremy Paul Francisco GONZALEZ ,  Norman Bruno Andre JODET

IPC: F02K1/34 ,  F02K1/38 ,  F02K1/48

Abstract: The invention proposes an assembly for a rear of a dual-flow turbomachine (10) having a longitudinal axis (X), comprising: a secondary nozzle (110) defined about the longitudinal axis (X), said secondary nozzle being configured to eject a mixture of the flows coming from a secondary vein (Vs) and a primary vein (Vp) of the turbomachine (10), the secondary nozzle being of convergent-divergent form with a neck (112) corresponding to a minimal cross-cross-section of the secondary nozzle (110), a heating system located on at least one portion of the internal circumference of the secondary nozzle longitudinally in the region of the neck and/or upstream from the neck (112).