公开(公告)号：US12116928B2

公开(公告)日：2024-10-15

申请号：US18185007

申请日：2023-03-16

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David Menheere

IPC: F02C3/08 ,  F02C3/045 ,  F02C3/09 ,  F02C3/10 ,  F02C3/107 ,  F02C3/13 ,  F02C6/20 ,  F02C7/36

CPC classification number: F02C3/085 ,  F02C6/20 ,  F02C3/045 ,  F02C3/08 ,  F02C3/09 ,  F02C3/10 ,  F02C3/103 ,  F02C3/107 ,  F02C3/13 ,  F02C7/36

Abstract: An aircraft engine, has: a high-pressure spool having a high-pressure turbine drivingly engaged to a high-pressure compressor; and a low-pressure spool having: a first low-pressure turbine downstream of the high-pressure turbine; and a second low-pressure turbine downstream of the first low-pressure turbine, one or more of the first low-pressure turbine and the second low-pressure turbine drivingly engaged to a rotatable load, the first low-pressure turbine and the second low-pressure turbine radially offset from one another relative to a central axis of the aircraft engine.

公开(公告)号：US12110820B2

公开(公告)日：2024-10-08

申请号：US18241447

申请日：2023-09-01

Applicant: Rolls-Royce North American Technologies, Inc.

Inventor： Steven Mazur ,  Rex M. Little

IPC: F02C3/14 ,  F01D25/12 ,  F02C3/08 ,  F02C6/08

CPC classification number: F02C3/14 ,  F01D25/12 ,  F02C3/08 ,  F02C6/08

Abstract: A gas turbine engine includes a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the compressor and a fan, shaft, or propeller.

公开(公告)号：US20240200493A1

公开(公告)日：2024-06-20

申请号：US18565281

申请日：2022-06-30

Applicant: SAFRAN POWER UNITS

Inventor： Laurent Stéphane Tardy ,  Jaime Georges Paul Culla

IPC: F02C7/045 ,  B64D33/02 ,  B64D41/00 ,  F02C3/08

CPC classification number: F02C7/045 ,  B64D33/02 ,  B64D41/00 ,  F02C3/08 ,  B64D2033/0206 ,  B64D2033/0213 ,  F05D2220/50 ,  F05D2260/96

Abstract: The invention relates to an acoustic insulation assembly for an auxiliary power unit having a centrifugal compressor (1), comprising a ring-shaped casing (8) for an air inlet (3) and comprising a plurality of reinforcing arms (9) connecting its inner walls, a plurality of removable mechanical acoustic insulation parts (10), each mechanical part (10) being ring-shaped and comprising attachment means (11) intended to engage with the casing (8), such that the mechanical part (10) and the flow surface of the casing (8), defined by a pair of reinforcing arms (9), overlie one another.

公开(公告)号：US20230392546A1

公开(公告)日：2023-12-07

申请号：US18248998

申请日：2021-10-19

Applicant: INDIAN INSTITUTE OF TECHNOLOGY, KHARAGPUR

Inventor： CHETANKUMAR SURESHBHAI MISTRY ,  AKCHHAY KUMAR

IPC: F02C3/08 ,  F04D3/00 ,  F04D1/06

CPC classification number: F02C3/08 ,  F04D3/00 ,  F04D1/06

Abstract: The present invention is directed to axial-centrifugal contra-rotating compressor system comprising combination of contra-rotating axial compressor stage with a back end centrifugal compressor stage, eliminating stator blades, an inter-stage connecting duct at the entry of the centrifugal compressor and an discharge 5 diffuser at the exit of centrifugal compressor rotor characterized by radial to axial turning annular passage as per the gas turbine engine requirement, favouring reduction in engine size, weight, number of parts, overall engine length and produces a higher-pressure rise and swirl-free discharge towards the combustion chamber. The first low-pressure rotor having at least one axial blading assembly 10 rotates in the direction opposite to the second high-pressure rotor blading assembly comprising of at least one axial rotor and one centrifugal rotor. The blades for axial compressor are adopted of low-aspect ratio configuration for reliable high load stall free operation. The inter-stage connecting duct minimizes total pressure loss. The discharge diffuser recovers higher exit velocity and hence 15 higher kinetic energy.

公开(公告)号：US11753989B2

公开(公告)日：2023-09-12

申请号：US18164073

申请日：2023-02-03

Applicant: HONDA MOTOR CO., LTD.

Inventor： Shu Taguchi

IPC: F03B1/00 ,  F02C3/08 ,  F01D9/04

CPC classification number: F02C3/08 ,  F01D9/041 ,  F05D2200/13 ,  F05D2200/14 ,  F05D2260/96

Abstract: A turbomachinery includes a casing, a rotor shaft rotatably attached to the casing, a first blade row fixed to either one of the rotor shaft or the casing, and a second blade row fixed to either one of the rotor shaft or the casing and arranged adjacent to the upstream side or downstream side of the first blade row, wherein the turbomachinery sets the number of first blades and the number of second blades in a manner that the interblade phase angle difference of the second blade row is ±180°.

公开(公告)号：US09915199B2

公开(公告)日：2018-03-13

申请号：US13646783

申请日：2012-10-08

Applicant: United Technologies Corporation

Inventor： Sohail Mohammed

IPC: F02C3/08 ,  F02C3/09 ,  F04D29/28 ,  F04D29/32

CPC classification number: F02C3/09 ,  F02C3/08 ,  F04D29/284 ,  F04D29/324 ,  F05D2220/326 ,  F05D2220/36

Abstract: A fan rotor has a hub, and a plurality of axial flow fan blades extending radially outwardly of the hub. A radial compressor impeller is positioned radially inwardly of the fan blades. The radial compressor impeller has an upstream inlet which extends generally in an axial direction defined by an axis of rotation of the hub. The radial flow compressor impeller has an outlet that extends radially outwardly of the inlet, and into a supply passage for supplying air to a core engine. An engine is also disclosed.

公开(公告)号：US09650953B2

公开(公告)日：2017-05-16

申请号：US13604579

申请日：2012-09-05

Applicant: Bjoern Veith ,  Carlos Simon-Delgado ,  Daniel Seng ,  Andreas Haubitz

Inventor： Bjoern Veith ,  Carlos Simon-Delgado ,  Daniel Seng ,  Andreas Haubitz

IPC: F01D25/12 ,  F02C3/04 ,  F01D5/08 ,  F02C3/08 ,  F02C7/18

CPC classification number: F02C3/04 ,  F01D5/081 ,  F01D5/082 ,  F01D25/12 ,  F02C3/08 ,  F02C7/18

Abstract: A gas turbine is provided and includes a compressor, which via an air intake inducts and compresses air; a combustion chamber, in which a fuel is combusted using the compressed air, producing a hot gas; and a turbine, equipped with turbine blades, in which the hot gas is expanded, performing work. A first device is provided in order to cool turbine blades with compressed cooling air. The first device includes at least one separate compressor stage which produces compressed cooling air independently of the compressor.

公开(公告)号：US20160102608A1

公开(公告)日：2016-04-14

申请号：US14787662

申请日：2014-04-29

Applicant: XEICLE LIMITED

Inventor： Robert Gulliver LYNN

IPC: F02C3/36 ,  F02C7/22 ,  F02C7/24 ,  F02C7/28 ,  F01D9/02 ,  F23R3/00 ,  F23R3/28 ,  F23R3/42 ,  F01D25/24 ,  F02C3/04 ,  F02C7/14

CPC classification number: F02C3/36 ,  F01D9/02 ,  F01D15/08 ,  F01D25/24 ,  F02C3/04 ,  F02C3/08 ,  F02C3/16 ,  F02C3/165 ,  F02C7/14 ,  F02C7/222 ,  F02C7/24 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2240/50 ,  F05D2240/55 ,  F05D2260/85 ,  F05D2300/121 ,  F05D2300/2261 ,  F05D2300/2283 ,  F05D2300/603 ,  F23R3/002 ,  F23R3/007 ,  F23R3/28 ,  F23R3/42 ,  Y02E20/16 ,  Y02T50/672 ,  Y02T50/6765

Abstract: A rotor assembly for an engine, comprising: a rotor, supported on bearings for axial rotation, a rotor portion forming a compression passage extending outwards from the axis, gases entering the rotor through inlets at the axis and flowing outwards through the compression passage; a combustion chamber supported within the compression passage near the maximum radius of the rotor having a closed outer end and combustion chamber gases inlets through which gases enter the combustion chamber, each combustion chamber having a fuel inlet, and; one or more expansion passages in fluidic connection with and extending radially inwards from the combustion chamber within a compression passage and fluidically connecting at or near the rotor axis to a combustion gas outlet tube that extends along the rotor axis, combustion gases created by combustion of fuel with inlet gases within the combustion chamber expanding as they flow inwards through the expansion passage.

Abstract translation: 一种用于发动机的转子组件，包括：转子，支撑在用于轴向旋转的轴承上，转子部分形成从轴线向外延伸的压缩通道，通过入口在轴线处进入转子并向外流过压缩通道的气体; 在压缩通道内靠近转子的最大半径附近的燃烧室具有封闭的外端和燃烧室气体入口，气体进入燃烧室，每个燃烧室具有燃料入口， 与压缩通道内的燃烧室流体连接并径向向内延伸的一个或多个膨胀通道，并且在转子轴线处或其附近流体连接到沿着转子轴线延伸的燃烧气体出口管，由燃料燃烧产生的燃烧气体 当燃烧室内的入口气体向内流过膨胀通道时膨胀。

公开(公告)号：US20160084090A1

公开(公告)日：2016-03-24

申请号：US14844082

申请日：2015-09-03

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill ,  Mark F. Zelesky

IPC: F01D5/18 ,  F02C3/08 ,  F01D11/00

CPC classification number: F01D5/18 ,  F01D5/06 ,  F01D5/185 ,  F01D5/186 ,  F01D5/187 ,  F01D11/001 ,  F01D11/003 ,  F01D11/005 ,  F02C3/08 ,  F05D2220/32 ,  F05D2260/20 ,  Y02T50/676

Abstract: A turbine section includes a rotor assembly which includes an internal cooling passage. A segmented seal is adjacent the rotor assembly and includes a fluid passage that is in fluid communication with the internal cooling passage.

Abstract translation: 涡轮部分包括包括内部冷却通道的转子组件。 分段密封件邻近转子组件并且包括与内部冷却通道流体连通的流体通道。

公开(公告)号：US20150337894A1

公开(公告)日：2015-11-26

申请号：US14652973

申请日：2013-12-16

Applicant: Masato YOSHINO ,  Hiroki FUJIWARA

Inventor： Masato YOSHINO ,  Hiroki FUJIWARA

IPC: F16C17/02 ,  F01D25/16 ,  F16C32/06

CPC classification number: F16C17/024 ,  F01D25/16 ,  F01D25/166 ,  F02C3/08 ,  F02C7/06 ,  F02C7/08 ,  F05D2220/32 ,  F05D2220/40 ,  F16C27/02 ,  F16C32/0607 ,  F16C33/101 ,  F16C43/02 ,  F16C2360/23 ,  F16C2360/24

Abstract: A foil bearing includes an outer member (11), and a plurality of foils (13) that are mounted to an inner circumferential surface (11a) of the outer member (11) and directly face the inner circumferential surface (11a) of the outer member (11) in a radial direction without interposition of another member (such as back foils). The foils (13) each include: holding portions (13a, 13b) that are formed at both circumferential ends and held while in contact with the outer member (11); and a body portion (13c) that is formed circumferentially between the holding portions (13a, 13b) and has a bearing surface (A). At least an end portion on one side in a circumferential direction of the body portion (13c) is raised radially inward with respect to the inner circumferential surface (11a) of the outer member (11).

Abstract translation: 箔片轴承包括外部构件（11）和安装到外部构件（11）的内周面（11a）并直接面向外部构件（11）的内周面（11a）的多个箔片（13） （11），而不插入另一个部件（例如背部箔片）。 箔片（13）各自包括：保持部（13a，13b），其形成在两个圆周端并与外部构件（11）接触时保持; 以及在所述保持部（13a，13b）之间周向形成并具有支承面（A）的主体部（13c）。 主体部（13c）的圆周方向一侧的至少一端部相对于外侧部件（11）的内周面（11a）向内侧径向升高。