公开(公告)号：US12025060B2

公开(公告)日：2024-07-02

申请号：US17324404

申请日：2021-05-19

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Martin Drolet ,  Yves Cloutier

IPC: F02C9/28 ,  F02C7/36

CPC classification number: F02C9/28 ,  F02C7/36 ,  F05D2220/323 ,  F05D2270/021 ,  F05D2270/101 ,  F05D2270/3011 ,  F05D2270/303 ,  F05D2270/3061 ,  F05D2270/71

Abstract: Methods and systems for operating an aircraft engine having a compressor are described. The method comprises determining, based on actual operating parameters of the aircraft engine, a compressor mass flow limit for an aerodynamic stability of the aircraft engine; determining an actual compressor mass flow of the compressor of the aircraft engine, wherein the actual compressor mass flow is based on measured values of the aircraft engine; comparing the actual compressor mass flow to the compressor mass flow limit; and governing operation of the aircraft engine to cause an alternative compressor mass flow when the actual compressor mass flow reaches or is anticipated to reach the compressor mass flow limit.

公开(公告)号：US20240035393A1

公开(公告)日：2024-02-01

申请号：US17876854

申请日：2022-07-29

Applicant: Pratt & Whitney Canada Corp.

Inventor： Damien Le Pape ,  Mark Cunningham

IPC: F01D21/00

CPC classification number: F01D21/003 ,  F05D2220/323 ,  F05D2260/30 ,  F05D2270/3011

Abstract: A system is provided for an aircraft. This aircraft system includes a gas turbine engine and a sensor system. The gas turbine engine includes an inlet and a compressor section. A flowpath projects radially inward into the gas turbine engine from the inlet and extends through the compressor section. The sensor system includes a plurality of static pressure sensors at least partially within the flowpath. The sensor system is configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors.

公开(公告)号：US11867070B1

公开(公告)日：2024-01-09

申请号：US17876854

申请日：2022-07-29

Applicant: Pratt & Whitney Canada Corp.

Inventor： Damien Le Pape ,  Mark Cunningham

IPC: F01D21/00

CPC classification number: F01D21/003 ,  F05D2220/323 ,  F05D2260/30 ,  F05D2270/3011

Abstract: A system is provided for an aircraft. This aircraft system includes a gas turbine engine and a sensor system. The gas turbine engine includes an inlet and a compressor section. A flowpath projects radially inward into the gas turbine engine from the inlet and extends through the compressor section. The sensor system includes a plurality of static pressure sensors at least partially within the flowpath. The sensor system is configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors.

公开(公告)号：US11859561B2

公开(公告)日：2024-01-02

申请号：US17643072

申请日：2021-12-07

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Yves Cloutier

IPC: F02C9/00

CPC classification number: F02C9/00 ,  F05D2220/323 ,  F05D2270/3011

Abstract: A method of determining an inlet total air pressure includes determining a first parameter indicative of a first inlet total air pressure. The method includes executing a sequence that includes: determining a mass air flow passing through the air inlet based on the first parameter, determining a Mach number of air passing through the air inlet based on the mass air flow, determining a static air pressure at the air inlet, determining an air pressure ratio based on the Mach number, generating a subsequent parameter indicative of the revised inlet total air pressure based on the air pressure ratio and the static air pressure, and substituting the subsequent parameter for the first parameter. The method includes executing at least one additional instance of the sequence with the subsequent parameter, and outputting the subsequent parameter as the inlet total air pressure.

公开(公告)号：US20180100504A1

公开(公告)日：2018-04-12

申请号：US15729117

申请日：2017-10-10

Applicant: ROLLS-ROYCE plc

Inventor： Martin K. YATES

IPC: F04C15/00 ,  F04C2/107 ,  F04C14/24 ,  F02C7/232 ,  F02C9/26

CPC classification number: F04C15/0026 ,  F02C7/232 ,  F02C9/26 ,  F04C2/107 ,  F04C2/18 ,  F04C14/24 ,  F04C2210/1044 ,  F04C2210/203 ,  F04C2240/50 ,  F04C2240/56 ,  F04C2270/175 ,  F05D2270/3011

Abstract: The present invention provides a gear pump having one or more gears with bearing shafts supported by respective pressure-loaded gear pump bearing blocks. Each pressure-loaded bearing block has: a bore adapted to receive the bearing shaft of a gear of the pump; a thrust face at one end adapted to slidingly engage with a side surface of the gear, and an opposing rear face at the other end, the pump being adapted such that, in use, pressurised fluid is supplied to the rear face to provide a hydraulic load urging the thrust face of the bearing block towards the side surface of the gear; and a seal carried by the rear face, the seal, in use, partitioning higher fluid pressure and lower fluid pressure portions of the rear face. The gear pump further has a pressure regulating valve arranged such that, in use, the fluid pressure difference between the higher and lower fluid pressure portions of the rear face of the bearing block is adjustable by the valve to vary said hydraulic load.

公开(公告)号：US20170284296A1

公开(公告)日：2017-10-05

申请号：US15084966

申请日：2016-03-30

Applicant: General Electric Company

Inventor： Brian Francis Nestico ,  Brian K. Kestner ,  Brandon Wayne Miller

IPC: F02C7/057 ,  B64D31/06 ,  B64D27/10 ,  F02C3/14 ,  F02C3/06

CPC classification number: F02C7/057 ,  B64D27/10 ,  B64D31/06 ,  F02C3/06 ,  F02C3/14 ,  F02C7/042 ,  F05D2210/44 ,  F05D2220/323 ,  F05D2270/101 ,  F05D2270/102 ,  F05D2270/3011 ,  F05D2270/44 ,  F05D2270/54

Abstract: Systems and methods for adjusting airflow distortion in a gas turbine engine using a secondary airflow passage assembly are disclosed. A gas turbine engine can include a compressor section, a combustion section, and a turbine section in series flow and defining at least in part an engine airflow path. A casing can enclose the gas turbine engine and be at least partially exposed to a bypass airflow. The gas turbine engine can further include a secondary airflow passage assembly comprising a door and a duct, the duct defining an inlet located on the casing, the duct defining an outlet in airflow communication with the engine airflow path, the duct comprising an airflow passage extending between the inlet and outlet. The door can be moveable between an open and closed position to allow a portion of the bypass airflow to flow through the airflow passage to adjust airflow distortion.

公开(公告)号：US20170268520A1

公开(公告)日：2017-09-21

申请号：US15070268

申请日：2016-03-15

Applicant: General Electric Company

Inventor： Curtis William Moeckel ,  Andrew Breeze-Stringfellow ,  Peter John Wood ,  Eric Andrew Falk

IPC: F04D27/00 ,  F02C9/20 ,  F04D29/56 ,  F02C9/18

CPC classification number: F04D27/002 ,  F02C9/18 ,  F02C9/20 ,  F04D27/001 ,  F04D27/0223 ,  F04D27/023 ,  F04D27/0246 ,  F05D2220/32 ,  F05D2220/3219 ,  F05D2270/1024 ,  F05D2270/3011 ,  F05D2270/3013 ,  F05D2270/3015 ,  F05D2270/304

Abstract: An apparatus and method of controlling a multi-stage compressor of a gas turbine engine having a front-block of stages with variable stator vanes (VSVs), a rear block of stages downstream of the front-block, and a bleed air off-take from at least one of the stages. The method includes sensing the pressure of the bleed air from the bleed air off-take and adjusting the position of the VSV for the front-block.

公开(公告)号：US09695831B2

公开(公告)日：2017-07-04

申请号：US14790583

申请日：2015-07-02

Applicant: Woodward, Inc.

Inventor： Alexander Benim

IPC: G01N7/20 ,  F04D27/00 ,  F04D27/02

CPC classification number: F04D27/001 ,  F04D27/02 ,  F05D2260/80 ,  F05D2270/101 ,  F05D2270/3011 ,  F05D2270/3013 ,  F05D2270/3015 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/335

Abstract: The subject matter of this specification can be embodied in, among other things, a method that includes receiving one or more surge value parameters, selecting a first value from a selected parameter of the one of the parameters, determining a moving average, determining a rate of change, identifying a first phase of a surge cycle based on determining that the rate of change exceeds a threshold rate change, memorializing the first value, the moving average value, and a first time index, receiving a second value of the selected parameter, identifying a second phase of the surge cycle, receiving a third value of the selected parameter, identifying a third phase of the surge cycle, and providing an indication that one or more compressor surge cycles have occurred.

公开(公告)号：US20160319838A1

公开(公告)日：2016-11-03

申请号：US15105041

申请日：2014-12-16

Applicant: MAN DIESEL & TURBO SE

Inventor： Alf-Peter TIEDTKE ,  Matthias WOLLNIK

IPC: F04D29/42 ,  F04D29/16 ,  F04D27/00 ,  F04D17/10

CPC classification number: F04D29/4213 ,  F04D17/10 ,  F04D27/001 ,  F04D29/162 ,  F05B2240/14 ,  F05B2240/20 ,  F05B2270/3011 ,  F05B2270/3015 ,  F05D2270/3011 ,  F05D2270/3015

Abstract: Compressor stage with a stator-side intake connection piece via which medium which is to be compressed can be introduced into the compressor stage in the region of the compressor stage, with a stator-side inflow channel via which the medium to be compressed can be conveyed in direction of a rotor-side impeller proceeding from the intake connection piece, wherein the impeller has a radially inner hub, a radially outer cover disk and impeller blades extending between the hub and the cover disk, wherein a plus measuring point and a minus measuring point are provided at the compressor stage for measuring the effective pressure at the compressor stage, and wherein the minus measuring point is positioned upstream of the impeller outside of the stator-side inflow channel in an annular gap which branches off from the inflow channel.

Abstract translation: 具有定子侧进气连接件的压缩机级，通过该定子侧进气连接件，待压缩的介质可以通过定子侧流入通道被输送到压缩机级的压缩机级，通过该定子侧流入通道可以输送被压缩的介质 在转子侧叶轮从进气连接件前进的方向上，其中叶轮具有径向内轮毂，径向外盖盘和在轮毂和盖盘之间延伸的叶轮叶片，其中加上测量点和负测量 在压缩机级设置有用于测量压缩机级的有效压力的点，其中负测量点位于从定子侧流入通道外侧的叶轮的上游以从流入通道分支的环形间隙中。

公开(公告)号：US20160281724A1

公开(公告)日：2016-09-29

申请号：US15042528

申请日：2016-02-12

Applicant: Michael T. MATHEIDAS ,  Stanley O. Uptigrove

Inventor： Michael T. MATHEIDAS ,  Stanley O. Uptigrove

IPC: F04D27/02 ,  F04D25/02 ,  F04D31/00 ,  F04D17/10

CPC classification number: F04D27/02 ,  F04D17/10 ,  F04D17/12 ,  F04D25/02 ,  F04D27/001 ,  F04D29/705 ,  F04D31/00 ,  F05D2270/101 ,  F05D2270/3011 ,  F05D2270/3013 ,  F05D2270/3061 ,  F05D2270/311 ,  F05D2270/54

Abstract: The disclosure includes controlling a pressure ratio for a compressing system, comprising introducing a quantity of liquid into an input stream to create a multiphase input stream, compressing the multiphase input stream with a centrifugal compressor to create a discharge stream, measuring a parameter of the discharge stream, wherein the discharge parameter corresponds to a pressure ratio for the centrifugal compressor, when the parameter exceeds a first predetermined point, increasing a pressure ratio of the centrifugal compressor by increasing the quantity of liquid introduced, and when the parameter exceeds a second predetermined point, decreasing the pressure ratio by decreasing the quantity of liquid introduced.

Abstract translation: 本公开包括控制压缩系统的压力比，包括将一定量的液体引入输入流以产生多相输入流，用离心式压缩机压缩多相输入流以产生排出流，测量放电参数 流，其中，当所述参数超过第一预定点时，所述排出参数对应于所述离心式压缩机的压力比，通过增加所引入的液体的量来增加所述离心式压缩机的压力比，并且当所述参数超过第二预定点 通过减少引入的液体的量来降低压力比。