公开(公告)号：US20240352870A1

公开(公告)日：2024-10-24

申请号：US18687520

申请日：2022-11-30

申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.

发明人： Satoshi Kumagai ,  Shunsuke Mizumi ,  Koji Ishibashi ,  Keisuke Uchino

IPC分类号： F01D21/00 ,  F01D25/24 ,  G01M3/26

CPC分类号： F01D21/003 ,  F01D25/243 ,  G01M3/26 ,  F05D2260/31 ,  F05D2260/83

摘要： A method for estimating a flange surface pressure distribution includes: a reference model receiving step of receiving a three-dimensional reference shape model of a rotary machine; a measured coordinate receiving step of receiving measured three-dimensional coordinate data at a plurality of positions on an upper flange surface and a lower flange surface when a casing is in an open state; a condition receiving step of receiving a tightening torque and an elastic coefficient of a plurality of bolts, elastic coefficients and weights of an upper-half casing and a lower-half casing, and the like; a modified model creating step of creating a three-dimensional modified shape model by modifying the three-dimensional reference shape model based on the measured three-dimensional coordinate data at the plurality of positions; and a pressure distribution estimating step of obtaining, by using the three-dimensional modified shape model and under the conditions received in the condition receiving step, a pressure distribution of a flange surface in a fastened state.

公开(公告)号：US20240338806A1

公开(公告)日：2024-10-10

申请号：US18578259

申请日：2022-07-15

申请人： Lufthansa Technik AG

发明人： Jan Oke PETERS ,  Lukas BECHHEIM ,  Lee-Roy AUTH

IPC分类号： G06T7/00 ,  B23P6/00 ,  F01D21/00 ,  G01N21/95 ,  G06T7/50

CPC分类号： G06T7/0002 ,  B23P6/002 ,  F01D21/003 ,  G01N21/9515 ,  G06T7/50 ,  F05D2260/83

摘要： The invention relates to a method (100) for supporting the processing of damage on a blading of a turbomachine (10) having a plurality of blades (11), comprising the following steps/stages: determining (103) a contour for processing (202) for mechanically processing a damaged area (20) of a first blade (11.1) of the blading and capturing (104) a first image (200) of a blade area (12) of the first blade (11.1) comprising the damaged area (20). The invention also relates to a computer program product and a system (1).

公开(公告)号：US20240328321A1

公开(公告)日：2024-10-03

申请号：US18127349

申请日：2023-03-28

申请人： Pratt & Whitney Canada Corp.

发明人： Masoud Roshan Fekr ,  Rana Foroutan ,  Robert Huszar

IPC分类号： F01D5/30

CPC分类号： F01D5/30 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/30 ,  F05D2260/83

摘要： A test blade for a blade release test, including: an airfoil extending radially from a platform; and a root portion secured to the platform, the root portion having an elongated opening extending longitudinally from a leading edge of the root portion towards a trailing edge of the root portion, wherein the elongated opening has a width extending along the leading edge of the root portion that is greater than or equal to 3 times a radial height of the elongated opening.

公开(公告)号：US20240309777A1

公开(公告)日：2024-09-19

申请号：US18594226

申请日：2024-03-04

申请人： ROLLS-ROYCE PLC

发明人： Guy STEVENSON

IPC分类号： F01D21/00 ,  F02C7/22 ,  G01K1/02 ,  G01K7/02 ,  G01K11/32

CPC分类号： F01D21/003 ,  F02C7/22 ,  G01K1/026 ,  G01K7/02 ,  G01K11/32 ,  F05D2260/83 ,  G01K2205/00

摘要： A temperature measurement system for a gas turbine engine, the gas turbine engine including, in axial flow sequence, a compressor section, a combustor section having plural fuel spray nozzles, and a turbine section. The temperature measurement system includes one or more optical thermometers, each optical thermometer configured to measure the temperature of a component washed by the working gas of the engine, the or each component being in the combustor section or the turbine section at a first position along the axis of the engine.

公开(公告)号：US20240263562A1

公开(公告)日：2024-08-08

申请号：US18611986

申请日：2024-03-21

申请人： General Electric Company

发明人： Eric R. Westervelt ,  Stefan Joseph Cafaro ,  James R. Reepmeyer ,  Terry Hei Tsun Ma

IPC分类号： F01D21/00 ,  F01D17/08 ,  F02C7/141 ,  F02C7/18 ,  F02C9/28

CPC分类号： F01D21/003 ,  F01D17/085 ,  F02C7/141 ,  F02C7/185 ,  F02C9/28 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/606 ,  F05D2260/80 ,  F05D2260/83

摘要： A method of transient control of a thermal transport bus of a turbomachine includes measuring a measured temperature and a measured pressure of a working fluid; determining a selected run state of a turbomachine, wherein the selected run state is one of a plurality of run states; selecting a desired operating condition comprising a desired temperature range and a desired pressure range as a function of a desired state of the working fluid; comparing the measured temperature with the desired temperature range, and comparing the measured pressure with the desired pressure range; and modulating control of the thermal transport bus as a function of the comparing of the measured temperature with the desired temperature range and the comparing of the measured pressure with the desired pressure range.

公开(公告)号：US12006830B2

公开(公告)日：2024-06-11

申请号：US17971183

申请日：2022-10-21

申请人： Pratt & Whitney Canada Corp.

发明人： Yongsheng Zhou ,  Brigitte Toljagic

IPC分类号： G01M15/14 ,  F01D5/34 ,  F01D21/00 ,  F01D21/04

CPC分类号： F01D21/003 ,  F01D5/34 ,  F01D21/045 ,  G01M15/14 ,  F05D2260/83

摘要： An integrally bladed rotor (IBR) for a gas turbine engine is provided. The IBR includes a hub, rotor blades that include a test blade, and at least one heating element. Each rotor blade has an airfoil with leading and trailing edges, suction side and pressure side surfaces, and a base end. The airfoil of the test blade includes at least one slot defining a void in the airfoil. The slot extends a lengthwise distance into the airfoil along a direction generally between the leading and trailing edges of the airfoil and terminates at a slot end surface. The airfoil includes at least one internal cavity extending lengthwise from the slot end surface. The heating element is disposed in the internal cavity and selectively produces thermal energy sufficient to heat the airfoil material proximate the internal cavity to a temperature at which the airfoil mechanical strength properties are decreased.

公开(公告)号：US11898453B1

公开(公告)日：2024-02-13

申请号：US17970361

申请日：2022-10-20

申请人： XI'AN JIAOTONG UNIVERSITY

发明人： Zhibo Yang ,  Jiahui Cao ,  Xuefeng Chen ,  Zengkun Wang ,  Laihao Yang ,  Shaohua Tian ,  Haoqi Li ,  Wenbo Li

IPC分类号： G01M15/14 ,  F01D21/00

CPC分类号： F01D21/003 ,  G01M15/14 ,  F05D2260/83 ,  F05D2270/304 ,  F05D2270/821

摘要： The present disclosure discloses a method for extracting a natural frequency difference between blades by a single blade tip timing sensor or uniformly distributed blade tip timing sensors. The method includes the following steps: acquiring actual arrival time of a rotating blade by using a single blade tip timing sensor or uniformly distributed blade tip timing sensors, and converting a difference between theoretical arrival time and the actual arrival time into displacement data of a blade tip according to a rotational speed and a blade length of the rotating blade; selecting displacement data of blade tips of two rotating blades with the same blade length at the same rotational speed; intercepting the displacement data, performing discrete Fourier transform respectively, and making a sampling frequency approximate to an average rotational speed to obtain spectrum data.

公开(公告)号：US11891903B2

公开(公告)日：2024-02-06

申请号：US17724035

申请日：2022-04-19

申请人： Pratt & Whitney Canada Corp.

发明人： Guy Lefebvre ,  Francois Doyon

IPC分类号： F01D21/00 ,  F02C7/00 ,  F02C7/18 ,  G01M15/02 ,  G01M15/14

CPC分类号： F01D21/003 ,  F02C7/00 ,  F02C7/18 ,  G01M15/02 ,  G01M15/14 ,  F05D2220/32 ,  F05D2260/83

摘要： A borescope plug assembly includes a housing, a plug, and a spring. The housing extends between a first housing end and a second housing end. The housing includes a plug aperture, an internal chamber, and a bayonet interface. The plug aperture is located at the second housing end. The internal chamber extends from the plug aperture toward the first housing end. The plug includes a shaft, a first sealing surface, and at least one tab. The shaft extends between a first shaft end and a second shaft end. The first sealing surface is disposed at the first shaft end. The at least one tab projects radially outward from the shaft. The plug extends through the plug aperture with the second shaft end and the at least one tab disposed within the internal chamber. The spring is positioned within the internal chamber between the first housing end and the at least one tab.

公开(公告)号：US20240003263A1

公开(公告)日：2024-01-04

申请号：US17854064

申请日：2022-06-30

申请人： General Electric Company

发明人： Richert Arthur Davis ,  Andrew F. King

IPC分类号： F01D21/00 ,  B22F10/28 ,  B22F10/37 ,  B22F12/63 ,  B22F5/00 ,  B33Y10/00 ,  B33Y80/00

CPC分类号： F01D21/003 ,  B22F10/28 ,  B22F10/37 ,  B22F12/63 ,  B22F5/009 ,  B33Y10/00 ,  B33Y80/00 ,  F05D2260/83

摘要： Calibration components having a turbomachine component form factor and methods of fabricating the calibration components using an additive manufacturing system are provided. A calibration component includes a main body and one or more representative quality indicators. The one or more representative quality indicators are disposed within the main body of the calibration component. The representative quality indicators include a cavity that has a material disposed within the cavity.

公开(公告)号：US20230359863A1

公开(公告)日：2023-11-09

申请号：US18022468

申请日：2021-08-23

申请人： David Alvord ,  David I. Pendleton ,  Aimee N. Williams ,  Georgia Tech Research Corporation

发明人： David Alvord ,  David I. Pendleton ,  Aimee N. Williams

IPC分类号： G06N3/045 ,  G01M15/14 ,  F02K9/96 ,  G06N3/0985

CPC分类号： G06N3/045 ,  F02K9/96 ,  G01M15/14 ,  G06N3/0985 ,  F05D2260/83

摘要： An exemplary virtual sensing method and system are disclosed for predictive reliability (VIPR) procedure and/or controls that employ artificial intelligence and machine learning (AI/ML), particularly deep neural networks and multi-modal deep learning, with vehicle sensor data to create virtual sensors. The virtual sensors can be used to estimate measurements and operating conditions in a hostile environment in rockets and vehicle systems.