公开(公告)号：US10514002B2

公开(公告)日：2019-12-24

申请号：US15271541

申请日：2016-09-21

申请人： United Technologies Corporation

发明人： Francis R. Moon ,  Daniel B. Kupratis

IPC分类号： F02K1/12 ,  F02K3/077 ,  F02K1/06 ,  F02K1/36 ,  F02K1/46 ,  F02K1/38 ,  F02K3/06

摘要： A gas turbine engine includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is included inboard of the outer case structure. An inner case structure is included inboard of the intermediate case structure. A variable area exhaust mixer is included, which is movable between a closed position adjacent to the intermediate case structure and an open position adjacent to the inner case structure.

公开(公告)号：US10451001B2

公开(公告)日：2019-10-22

申请号：US14947210

申请日：2015-11-20

申请人： Rolls-Royce Corporation

发明人： Jagdish S. Sokhey

IPC分类号： F02K1/38 ,  F01D25/28 ,  F02K1/80 ,  F02K1/48

摘要： An exhaust mixing system having an attachment flange configured to couple a lobed Oxide-CMC exhaust mixer to a turbine engine. The attachment flange includes an annulus and a plurality of projections extending from the annulus in a first direction that is substantially parallel to a central axis of the annulus. The annulus is configured to couple to the turbine engine and the plurality of projections is configured to couple to the lobed mixer.

公开(公告)号：US20190203620A1

公开(公告)日：2019-07-04

申请号：US16292846

申请日：2019-03-05

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Andre JULIEN ,  Serge DUSSAULT ,  Jean THOMASSIN

IPC分类号： F01N3/05 ,  B64D27/08 ,  B64D33/04 ,  F02B61/04 ,  F02B53/14 ,  F01N13/08 ,  B64D27/02 ,  F02C7/18 ,  F02C6/20 ,  F02C5/00 ,  F02K1/38 ,  B64D33/10 ,  B64D27/10

CPC分类号： F01N3/055 ,  B64D27/02 ,  B64D27/08 ,  B64D27/10 ,  B64D33/04 ,  B64D33/10 ,  F01N13/082 ,  F01N2260/022 ,  F01N2270/02 ,  F02B53/14 ,  F02B61/04 ,  F02B2053/005 ,  F02C5/00 ,  F02C6/206 ,  F02C7/18 ,  F02K1/386 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/676

摘要： A turboprop engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system, an air duct in fluid communication with an environment of the aircraft, a heat exchanger received within the air duct having coolant passages in fluid communication with the liquid coolant system and air passages air passages in fluid communication with the air duct, and an exhaust duct in fluid communication with an exhaust of the internal combustion engine. The exhaust duct has an outlet positioned within the air duct downstream of the heat exchanger and upstream of an outlet of the air duct, the outlet of the exhaust duct spaced inwardly from a peripheral wall of the air duct. In use, a flow of cooling air surrounds a flow of exhaust gases. A method of discharging air and exhaust gases in an turboprop engine assembly having an internal combustion engine is also discussed.

公开(公告)号：US10240560B2

公开(公告)日：2019-03-26

申请号：US14547857

申请日：2014-11-19

申请人： Rohr, Inc.

发明人： Stephen H. Ward

IPC分类号： B23P6/00 ,  F02K1/38

摘要： Aspects of the disclosure are directed to a system that includes a boot configured to attach to a chevron of an aircraft nacelle, and an attachment mechanism configured to attach the boot and the chevron. In some embodiments, a boot includes a first surface and a second surface, where the surfaces are attached by inwardly tapering sidewalls that form an opening that is configured to surround a chevron of an aircraft nacelle. In some embodiments, a repair of a chevron on an exhaust nozzle of an aircraft engine includes placing a chevron-shaped boot with a pocket over at least a portion of a chevron structure on an exhaust nozzle of an aircraft engine, the pocket having a shape that generally conforms to an external surface of the chevron, covering the portion of the chevron structure with the boot, and fastening the boot to the chevron through at least one of bonding or mechanical fastening.

公开(公告)号：US20190078466A1

公开(公告)日：2019-03-14

申请号：US16140782

申请日：2018-09-25

申请人： HONEYWELL INTERNATIONAL INC.

发明人： Nick Nolcheff

IPC分类号： F01D25/16 ,  F01D25/24 ,  F01D9/06 ,  F01D9/00 ,  F01D9/02 ,  F01D9/04 ,  F02C7/04 ,  F23R3/26 ,  F02C9/16 ,  F02C7/042 ,  F02K1/38 ,  F02K1/28 ,  F02K1/30 ,  F02K1/00 ,  F02K1/46

摘要： The present disclosure provides systems and apparatuses for use in turbine systems that integrate structural frame elements into a variable-vectoring flow control configuration in order to reduce the weight and length of such turbine systems. In one exemplary embodiment, an apparatus for directing a gas flow includes an annular outer structural casing, an annular central hub disposed within the outer structural casing, and a plurality of structural support elements extending radially between the central hub and the outer structural casing. The apparatus further includes a plurality of positionally-fixed, variable-vectoring flow control bodies extending radially between the central hub and the outer structural casing and positioned circumferentially along the central hub between ones of the plurality of structural support elements.

公开(公告)号：US10197007B2

公开(公告)日：2019-02-05

申请号：US14995661

申请日：2016-01-14

申请人： General Electric Company

发明人： Durga Srinivas Chillapalli ,  Hemanth Gudibande Sathyakumar Kumar ,  Bhaskar Nanda Mondal ,  Kishanjit Pal ,  Sushilkumar Gulabrao Shevakari ,  Thomas Ory Moniz

IPC分类号： F02K1/06 ,  F02K1/38 ,  F02K3/06 ,  F02C7/18

摘要： A variable core cowl vent nozzle system is described herein, the system including a core casing at least partially surrounding a core engine of a gas turbine engine, and a core cowl extending aftward from the core casing. The core cowl defines a core cowl vent area between the core cowl and a primary nozzle. At least one of the core cowl and the primary nozzle is movable to vary the core cowl vent area. A method for varying the core cowl vent area by moving one or more of the core cowl and the primary nozzle is also described herein.

公开(公告)号：US10094334B2

公开(公告)日：2018-10-09

申请号：US14172060

申请日：2014-02-04

申请人： The Boeing Company

发明人： Matthew D. Moore ,  Edward C. Marques

IPC分类号： F02K1/48 ,  F02K3/02 ,  F02K1/38 ,  F02K1/72 ,  F02K1/76 ,  F02K1/82 ,  F02K3/077 ,  B64D33/02

摘要： A method of controlling plume exhaust heat and/or noise radiation from a turbofan engine assembly having a short nacelle. A mixer duct shell is supported such that a downstream edge of the short nacelle overlays an upstream portion of the mixer duct shell. A first portion of fan exhaust may be routed through the mixer duct shell between its inner surface and an outer surface of a core engine shroud. A second portion of fan exhaust may be routed over an outer surface of the mixer duct shell. At least one of the inner surface and an outer surface of the mixer duct shell may have an acoustic lining including a honeycomb core structure.

公开(公告)号：US10018150B2

公开(公告)日：2018-07-10

申请号：US15137257

申请日：2016-04-25

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Remo Marini ,  Mark Huzzard Cunningham ,  Francois C. Bisson ,  Reza Mohammad Kameshki

IPC分类号： F02K1/38 ,  F02K1/48 ,  F02K3/06 ,  F01D9/04

CPC分类号： F02K1/48 ,  F01D9/041 ,  F02K1/386 ,  F02K3/06 ,  F05D2210/40 ,  F05D2250/61

摘要： A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer for mixing exhaust gases with a bypass air stream, the TEC comprising an annular hub and the mixer surrounding the hub, and a plurality of deswirling struts circumferentially spaced apart with respect to a central axis of the TEC and located entirely within an axial length of the mixer. The mixer defines a trailing edge having one or more upstream-most locations thereof where the mixing of the exhausted gases and the bypass air stream begins to take place. The deswirling struts each extend radially across the annular exhaust gas duct and interconnect the mixer and the hub, defining a trailing edge positioned upstream of and axially spaced away from the one or more upstream-most locations of the trailing edge of the mixer.

公开(公告)号：US20180003128A1

公开(公告)日：2018-01-04

申请号：US15686052

申请日：2017-08-24

申请人： Jetoptera, Inc.

发明人： Andrei Evulet

IPC分类号： F02K1/30 ,  F02K1/38

CPC分类号： F02K1/30 ,  F02B27/06 ,  F02B37/00 ,  F02B39/04 ,  F02C3/04 ,  F02C7/143 ,  F02K1/36 ,  F02K1/38 ,  F05D2260/4023 ,  F05D2260/601 ,  F05D2270/173 ,  F05D2270/18 ,  F05D2300/6033 ,  F23R3/22 ,  Y02T10/144 ,  Y02T10/146 ,  Y02T50/672

摘要： A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

公开(公告)号：US09714608B2

公开(公告)日：2017-07-25

申请号：US14343155

申请日：2012-09-05

申请人： Jagdish S. Sokhey ,  Anthony F. Pierluissi

发明人： Jagdish S. Sokhey ,  Anthony F. Pierluissi

IPC分类号： F02K1/36 ,  F02C3/04 ,  F02K1/38 ,  F02K3/02 ,  F02K3/077

CPC分类号： F02C3/04 ,  F02K1/36 ,  F02K1/383 ,  F02K1/386 ,  F02K3/025 ,  F02K3/077

摘要： One embodiment of the present invention is a unique gas turbine engine system. Another embodiment is a unique exhaust nozzle system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine systems and exhaust nozzle systems for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.