公开(公告)号：US20180266272A1

公开(公告)日：2018-09-20

申请号：US15919646

申请日：2018-03-13

Applicant: Nuovo Pignone Tecnologie Srl

Inventor： Antonio ASTI ,  Miriam LOSAPIO ,  Mariateresa PACI

IPC: F01D21/12 ,  F01D21/00 ,  F01D21/16

CPC classification number: F01D21/12 ,  F01D17/085 ,  F01D21/003 ,  F01D21/16 ,  F02C9/28 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/80 ,  F05D2260/83 ,  F23N5/022 ,  F23N5/245 ,  F23N2031/06 ,  F23N2041/20 ,  G01K3/14 ,  G01K13/02 ,  G01K2013/024

Abstract: The method is used for detecting one failure in a burner of a combustor of a turbine system; the combustor comprises a plurality of burners arranged annularly; the turbine system comprises a turbine downstream of the combustor, the method comprising the steps of: A) providing a plurality of temperature sensors arranged annularly at the outlet of the turbine, B) detecting a plurality of temperatures through the plurality of temperature sensors, C) calculating a temperature spread indicator as a function of the plurality of temperatures, and D) carrying out a comparison the temperature spread indicator and a threshold; a positive result of this comparison indicates a burner failure.

公开(公告)号：US10080068B2

公开(公告)日：2018-09-18

申请号：US15114234

申请日：2015-02-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Kurt J. Sobanski

IPC: H04B17/00 ,  H04Q1/02 ,  H04Q9/00 ,  H01Q5/55 ,  F01D21/00 ,  H04L12/24 ,  H04Q1/28 ,  F02K3/06 ,  G07C5/00 ,  H04B15/02 ,  H04W12/04 ,  G01M15/14 ,  H04B1/02 ,  F02C3/04 ,  F02C9/00 ,  H01P3/12 ,  H01P5/02 ,  H05K9/00 ,  H04L12/40 ,  G06K7/10 ,  G07C5/08 ,  F02K3/04 ,  H04B1/3822 ,  H04B1/00 ,  H04L29/08 ,  H04W84/18 ,  H04W84/12

CPC classification number: H04Q1/116 ,  F01D21/003 ,  F02C3/04 ,  F02C9/00 ,  F02K3/04 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2260/80 ,  F05D2270/54 ,  F05D2270/80 ,  G01M15/14 ,  G06K7/10188 ,  G07C5/008 ,  G07C5/0808 ,  H01P3/122 ,  H01P5/02 ,  H01Q5/55 ,  H04B1/02 ,  H04B1/3822 ,  H04B15/02 ,  H04B15/025 ,  H04L12/40045 ,  H04L41/0803 ,  H04L67/10 ,  H04L67/12 ,  H04L2012/40273 ,  H04Q1/28 ,  H04Q9/00 ,  H04Q2209/40 ,  H04W12/04 ,  H04W84/12 ,  H04W84/18 ,  H05K9/0081

Abstract: A system for a machine component includes at least one local transmitter/receiver. At least one device is associated with a component and configured to communicate with the at least one local transmitter/receiver through wireless signals. Shielding surrounds both the local transmitter and the device for containing the wireless signals proximate to the component. A remote processing unit is disposed outside of the shielding in communication with the local transmitter/receiver. A control system and method are also disclosed.

公开(公告)号：US20180259436A1

公开(公告)日：2018-09-13

申请号：US15919986

申请日：2018-03-13

Applicant: KING FAHD UNIVERSITY OF PETROLEUM AND MINERALS

Inventor： Jafar Al-Bin-Mousa ,  Ahmad Al-Ghamdi ,  Kamal Al-Shareef ,  Abdulrahman Al-Adsani

IPC: G01N3/42 ,  G01N3/18 ,  G01N19/04 ,  G01N3/54 ,  F01D5/28 ,  F01D25/28

CPC classification number: G01N3/42 ,  F01D5/288 ,  F01D21/003 ,  F01D25/285 ,  F05D2230/40 ,  F05D2230/90 ,  F05D2260/80 ,  F05D2260/83 ,  G01N3/18 ,  G01N3/54 ,  G01N19/04 ,  G01N2033/0003 ,  G01N2203/0078 ,  G01N2203/0226

Abstract: An indentation tester and indentation method for testing a sample heated at a temperature range from above 800° C. to 1200° C., and above, is disclosed. The indentation tester includes a stage having a metallic cylindrical base that houses an inner cylindrical base made of a temperature resistant material sufficient to maintain shape over the range of the heating temperature. A removable crown fastens to the cylindrical base and includes a ring that holds an axisymmetric pipe made of a temperature resistant material sufficient to maintain shape over the range of heated temperature. A nut is turned to tighten the pipe which secures the sample and guides an indenter to penetrate the sample. The indenter includes a rod made of temperature resistant material and a indenter tip.

公开(公告)号：US20180252117A1

公开(公告)日：2018-09-06

申请号：US15450939

申请日：2017-03-06

Applicant: United Technologies Corporation

Inventor： Eli Cole Warren ,  Darren M. Wind ,  Ian Alexander Fielder Agoos

IPC: F01D21/00 ,  G01B21/16

CPC classification number: F01D21/003 ,  F01D11/025 ,  F01D11/12 ,  F01D17/02 ,  F05D2250/232 ,  F05D2260/80 ,  G01B21/16

Abstract: In combination a wear indicator and a component of a gas turbine engine is provided. The wear indicator is secured to a surface of the component of the gas turbine engine. The wear indicator comprising: a first side delaminates when impacted by a blade of the gas turbine engine; a second side parallel to the first side, the second side being secured to a surface of the component of the gas turbine engine; a mid-section interposed between the first side and the second side; and a reference dimension remains constant when the first side delaminates.

公开(公告)号：US10060284B2

公开(公告)日：2018-08-28

申请号：US14774519

申请日：2013-12-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Xuejun Liu ,  Matthew R. Feulner

IPC: G01K13/02 ,  F01D17/08 ,  F01D21/00 ,  B64D33/00

CPC classification number: F01D17/085 ,  B64D33/00 ,  F01D21/003 ,  F05D2260/80 ,  G01K13/02 ,  G01K13/028 ,  G01K2013/024 ,  G01K2205/02

Abstract: A total air temperature (TAT) sensor assembly is disclosed. The assembly includes a housing that accommodates a temperature sensor. The assembly also includes a first airfoil that includes a leading end and a trailing end and a second airfoil that includes a leading end and a trailing end. The first and second airfoils are disposed in a spaced-apart fashion that defines a curved passageway so incoming air can flow between the first and second airfoils before engaging the housing and the temperature sensor. The trailing ends of the airfoils are disposed on opposite sides of the housing and spaced apart from the housing to permit air flowing through the curved passageway to pass the housing.

公开(公告)号：US10051345B2

公开(公告)日：2018-08-14

申请号：US15255716

申请日：2016-09-02

Applicant: United Technologies Corporation

Inventor： Joseph V. Mantese ,  Kurt J. Sobanski ,  Brian L. McCabe ,  Joseph Zacchio

IPC: H04B17/00 ,  H04Q1/02 ,  F01D21/00 ,  H04B1/00

CPC classification number: H04Q1/116 ,  F01D21/003 ,  F05D2260/80 ,  Y02T50/671

Abstract: A system of a machine is provided. The system having: a network of a plurality of sensing/control/identification devices distributed throughout the machine, at least one of the plurality of sensing/control/identification devices associated with at least one sub-system component of the machine and operable to communicate through a plurality of electromagnetic signals; shielding surrounding at least one of the sensing/control/identification devices to contain the electromagnetic signals proximate to the at least one sub-system component; and a remote processing unit operable to communicate with the network of the sensing/control/identification devices through the electromagnetic signals, wherein the at least one of the plurality of sensing/control/identification devices has internal memory independent of the remote processing unit, the internal memory having historical data corresponding to the least one sub-system component.

公开(公告)号：US20180216481A1

公开(公告)日：2018-08-02

申请号：US15420793

申请日：2017-01-31

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

Inventor： Aaron D. Sippel ,  Brian J. Shoemaker ,  Ted J. Freeman

IPC: F01D11/12 ,  F01D25/00 ,  F01D5/02 ,  F01D21/00 ,  F01D9/04

CPC classification number: F01D11/122 ,  F01D21/003 ,  F05D2230/90 ,  F05D2240/11 ,  F05D2260/80 ,  F05D2300/6033

Abstract: Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assembly includes a turbine wheel assembly and a turbine shroud. The turbine wheel assembly includes a disk and a plurality of blades that extend outwardly from the disk in a radial direction away from an axis. The turbine shroud extends around the blades of the turbine wheel assembly to block gasses from passing over the blades during operation of the turbine assembly. The turbine shroud includes a plurality of blade track segments arranged circumferentially adjacent to one another about the axis to form a ring. Each blade track segment has a runner that forms a primary track surface facing the axis and spaced from the axis in the radial direction.

公开(公告)号：US10036275B2

公开(公告)日：2018-07-31

申请号：US14916378

申请日：2014-09-08

Applicant: Siemens Aktiengesellschaft

Inventor： Martin Ophey ,  Martin Bennauer ,  Thorsten Engler ,  Susanne Haas ,  Andreas Pahl ,  Marian-Peter Pieczyk ,  Martin Stapper ,  David Veltmann

IPC: F01D21/02 ,  F01D21/20 ,  F01D5/02 ,  F01D15/10 ,  F01D15/12 ,  F01K23/12 ,  G01M15/14 ,  F01D21/00

CPC classification number: F01D21/02 ,  F01D5/02 ,  F01D15/10 ,  F01D15/12 ,  F01D21/003 ,  F01K23/12 ,  F05D2220/31 ,  F05D2220/32 ,  F05D2220/76 ,  F05D2240/60 ,  F05D2260/83 ,  G01M15/14

Abstract: A method for testing an overspeed protection apparatus of a single-shaft system that includes: a) operating the system at nominal speed and under electrical load, wherein the load is selected to be low enough that, after dropping the load, the speed of the system rises such that the speed remains below steam turbine threshold speed lower than gas turbine threshold speed, such that first overspeed protection is triggered when the speed of the steam turbine reaches the steam turbine threshold speed, and second overspeed protection is triggered when the speed of the gas turbine reaches the gas turbine threshold speed; b) dropping the load; c) increasing the mass flow of the steam introduced into the steam turbine and/or of the fuel introduced into the gas turbine such that the speed of the steam turbine reaches the steam turbine threshold speed; d) testing whether the first overspeed protection is triggered.

公开(公告)号：US20180202315A1

公开(公告)日：2018-07-19

申请号：US15405491

申请日：2017-01-13

Applicant: Hamilton Sundstrand Corporation

Inventor： Joseph K. Coldwate

IPC: F01D21/12 ,  F01D5/02 ,  F01D15/10 ,  F01D21/00 ,  H02P27/06 ,  H02P6/17 ,  H02K7/18 ,  H02K7/14 ,  H02K11/25 ,  H02K11/33 ,  H02K7/116

CPC classification number: F01D21/12 ,  F01D5/02 ,  F01D15/10 ,  F01D21/003 ,  F01D25/36 ,  F05D2220/32 ,  F05D2220/764 ,  H02K7/14 ,  H02K7/1823 ,  H02K11/25 ,  H02P6/17 ,  H02P27/06 ,  H02P29/66 ,  Y02T50/671

Abstract: A motor arrangement includes a shaft, a motor with a cage winding fixed in rotation relative to the shaft, and a generator. The generator includes a permanent magnet assembly fixed in rotation relative to the shaft. The permanent magnet assembly and the cage winding are fixed in rotation relative to one another such that the generator generates a sinusoidal AC voltage signal according to an excitation phase applied to the motor for controlling rotor distortion during cool down of a gas turbine engine.

公开(公告)号：US10018071B2

公开(公告)日：2018-07-10

申请号：US15284745

申请日：2016-10-04

Applicant: General Electric Company

Inventor： Sarah Lori Crothers ,  Paige Marie Sopcic ,  Jason Dean Fuller ,  Daniel Joseph Flavin

IPC: F01D21/00 ,  G01M15/14 ,  G05B23/02

CPC classification number: F01D21/003 ,  F05D2220/30 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2270/804 ,  F05D2270/807 ,  F05D2270/808 ,  F05D2270/81 ,  G01M15/14 ,  G05B23/0216

Abstract: In one embodiment, a turbine system includes a number of sensors, each of the number of sensors disposed in a respective location of the turbine system, and a controller including a memory storing one or more processor-executable routines and a processor. The processor configured to access and execute the one or more routines encoded by the memory wherein the one or more routines, when executed cause the processor to receive one or more signals from the number of sensors during any stage of operation of the turbine system, and convert the one or more signals to audio output.