公开(公告)号：US20180087398A1

公开(公告)日：2018-03-29

申请号：US15278612

申请日：2016-09-28

Applicant: United Technologies Corporation

Inventor： Matthew P. Forcier ,  Joseph B. Staubach

IPC: F01D25/12 ,  F28D15/02 ,  F01D5/08

CPC classification number: F01D25/12 ,  F01D5/08 ,  F02C7/08 ,  F05D2220/36 ,  F05D2260/208 ,  F28D15/02 ,  F28D15/046 ,  F28D2021/0026 ,  F28F21/02 ,  Y02T50/671 ,  Y02T50/676

Abstract: A graphene heat pipe for a gas turbine engine includes a body of graphene. The body has a hot side to accept heat from the gas turbine engine, a cold side to reject heat from the body, and an adiabatic portion to flow heat within the body between the hot side and the cold side.

公开(公告)号：US09926846B2

公开(公告)日：2018-03-27

申请号：US14221216

申请日：2014-03-20

Applicant: ENER-CORE POWER, INC.

Inventor： Edan Prabhu

IPC: F02C7/22 ,  F02C3/22 ,  F02C6/18 ,  F02C7/10 ,  F02C9/40 ,  F02C7/08 ,  F02C9/26

CPC classification number: F02C7/22 ,  F02C3/22 ,  F02C6/18 ,  F02C7/08 ,  F02C7/10 ,  F02C9/26 ,  F02C9/40

Abstract: A fuel oxidizer system is operated in a first operating mode. In the first operating mode, a mixture that includes fuel from a fuel source is compressed in a compressor of the fuel oxidizer system; the fuel of the compressed mixture is oxidized in a reaction chamber of the fuel oxidizer system; and the oxidized fuel is expanded to generate rotational kinetic energy. The fuel oxidizer system is operated in a second operating mode. In the second operating mode, fuel from the fuel source is directed to bypass the compressor, and the fuel that bypassed the compressor is oxidized in the reaction chamber.

公开(公告)号：US09885283B2

公开(公告)日：2018-02-06

申请号：US14729318

申请日：2015-06-03

Applicant: Rolls-Royce Corporation

Inventor： Igor Vaisman ,  Thomas E. Bastnagel

IPC: F02C3/13 ,  F02C1/10 ,  F02C3/04 ,  F02C7/08 ,  F02C7/143 ,  F02K3/06 ,  F02K3/077 ,  F01K25/10 ,  F22B3/08 ,  F25B9/00 ,  F25B27/00 ,  F25B9/06

CPC classification number: F02C3/13 ,  F01K25/103 ,  F02C1/10 ,  F02C3/04 ,  F02C7/08 ,  F02C7/143 ,  F02K3/06 ,  F02K3/077 ,  F05D2210/10 ,  F05D2210/12 ,  F05D2210/20 ,  F05D2220/32 ,  F05D2260/213 ,  F22B3/08 ,  F25B9/008 ,  F25B9/06 ,  F25B27/00 ,  F25B2309/061 ,  F25B2327/00 ,  Y02T50/675

Abstract: A gas turbine engine includes a shaft having a first air compressor coupled thereto, a combustor positioned to receive compressed air from the first compressor, and a power source coupled to the shaft, the power source powered by a working fluid other than the compressed air.

公开(公告)号：US09810149B2

公开(公告)日：2017-11-07

申请号：US14378205

申请日：2013-02-15

Applicant: ICE INDUSTRIAL PROPERTIES BV

Inventor： Johannes Arjen Hoogland ,  George Johannes Kruijer

IPC: F02C7/10 ,  F02C1/04 ,  F02C7/08 ,  F02C7/105

CPC classification number: F02C7/10 ,  F02C1/04 ,  F02C7/08 ,  F02C7/105

Abstract: The invention is directed to a process to obtain a compressed gas starting from a starting gas having a lower pressure by performing the following steps: (i) increasing the pressure and temperature of a gas having an intermediate pressure by means of indirect heat exchange against a fluid having a higher temperature to obtain a gas high in pressure and temperature, (ii) obtaining part of the gas high in temperature and pressure as the compressed gas, (iii) using another part of the gas high in temperature and pressure as a driving gas to increase the pressure of the starting gas in one or more stages to obtain the gas having an intermediate pressure for use in step (i). The invention is also directed to a configuration wherein the process can be performed and directed to a process to generate energy using the process.

公开(公告)号：US09752501B2

公开(公告)日：2017-09-05

申请号：US14623939

申请日：2015-02-17

Applicant: PowerPHASE LLC

Inventor： Robert J. Kraft

IPC: F02C1/00 ,  F02C7/10 ,  F02C7/08 ,  F02C3/04 ,  F02C6/00 ,  H02K7/18

CPC classification number: F02C7/10 ,  F02C3/04 ,  F02C6/00 ,  F02C7/08 ,  H02K7/1823 ,  Y02E20/16

Abstract: The invention relates generally to electrical power systems, including generating capacity of a gas turbine, and more specifically to pressurized air injection that is useful for providing additional electrical power during periods of peak electrical power demand from a gas turbine system power plant, as well as to inlet heating to allow increased engine turn down during periods of reduced electrical demand.

公开(公告)号：US09724746B2

公开(公告)日：2017-08-08

申请号：US13804118

申请日：2013-03-14

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Andreas Eleftheriou ,  Daniel Alecu ,  David Menheere

IPC: B21D53/04 ,  F02K1/82 ,  F02C7/08 ,  F28F3/04 ,  F28F13/06 ,  B21D49/00 ,  F28F13/02 ,  F28D7/16 ,  F28D9/00 ,  F28D21/00

CPC classification number: B21D53/04 ,  B21D49/00 ,  F01D25/30 ,  F02C7/08 ,  F02K1/822 ,  F05D2210/34 ,  F05D2220/32 ,  F05D2250/711 ,  F05D2250/712 ,  F28D7/1684 ,  F28D9/0031 ,  F28D2021/0026 ,  F28F3/046 ,  F28F13/02 ,  F28F13/06 ,  Y02T50/672 ,  Y02T50/675 ,  Y10T29/49357

Abstract: A recuperator disposed in the exhaust duct of a gas turbine engine includes a plurality of recuperator plates arranged in a spaced-apart relationship to define therebetween a plurality of interstices and fluid channels, the plurality of interstices adapted to direct therethrough at least one first stream received at a leading plate edge of the recuperator plates and the plurality of fluid channels adapted to direct therethrough at least one second stream to effect heat exchange between the at least one first stream and the at least one second stream. Each recuperator plate includes, formed at the leading plate edge thereof, a first concavity extending along the leading edge in a direction substantially parallel to a longitudinal axis of the plate. The first concavity extends transversely to a direction of the at least one first stream flowing over each recuperator plate.

公开(公告)号：US20170184150A1

公开(公告)日：2017-06-29

申请号：US15460445

申请日：2017-03-16

Applicant: Masato YOSHINO ,  Hiroki FUJIWARA

Inventor： Masato YOSHINO ,  Hiroki FUJIWARA

IPC: F16C17/02 ,  F16C32/06 ,  F02C7/06 ,  F16C27/02

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).

公开(公告)号：US09664110B2

公开(公告)日：2017-05-30

申请号：US14492222

申请日：2014-09-22

Applicant: ALSTOM Technology Ltd

Inventor： Felix Guethe ,  Madhavan Narasimhan Poyyapakkam ,  Frank Graf ,  Bruno Schuermans ,  Eribert Benz

IPC: F02C3/34 ,  F02C7/08 ,  F23R3/28 ,  F23R3/26 ,  F23C9/00 ,  F02C3/13 ,  F23R3/04

CPC classification number: F02C3/34 ,  F02C3/13 ,  F02C7/08 ,  F23C9/00 ,  F23C2202/30 ,  F23R3/04 ,  F23R3/26 ,  F23R3/286

Abstract: The invention relates to a method for operating a gas turbine which includes a compressor with annular inlet area, at least two burners, a combustion chamber and a turbine. According to the method, at least one first partial intake flow, consisting of oxygen-reduced gas which has an oxygen concentration which is lower than the average oxygen concentration of the compressor intake flow, and at least one second partial intake flow, consisting of fresh air, are fed to the compressor in an alternating manner in the circumferential direction of the inlet area. In addition, the invention relates to a gas turbine power plant with a gas turbine, the compressor inlet of which includes at least one first segment and at least one second segment which are arranged in an alternating manner around a compressor inlet in the circumferential direction, wherein a feed for an oxygen-reduced gas is connected to the first segment and a fresh air feed is connected to the second segment of the compressor inlet.

公开(公告)号：US09447732B2

公开(公告)日：2016-09-20

申请号：US13685608

申请日：2012-11-26

Applicant: General Electric Company

Inventor： Indrajit Mazumder ,  Rajarshi Saha ,  Seyfettin Can Gulen ,  Sabarinath Devarajan ,  Prashant Kumar

IPC: F02C3/34 ,  F02C7/047 ,  F02C7/08 ,  F02C6/08 ,  F04D27/02 ,  F02C9/18

CPC classification number: F02C7/047 ,  F02C3/34 ,  F02C6/08 ,  F02C7/08 ,  F02C9/18 ,  F04D27/0207 ,  F04D27/0215

Abstract: Embodiments of the present disclosure are directed towards a system that includes a recirculation system. The recirculation system includes a compressor discharge air line extending from a compressor to an air intake. The compressor discharge air line is configured to flow a compressor discharge air flow, and the air intake is configured to supply an air flow to the compressor. An ejector is disposed along the compressor discharge air line between the compressor and the air intake. The ejector is configured to receive and mix the compressor discharge air flow and a turbine exhaust flow to form a first mixture.

Abstract translation: 本公开的实施例涉及包括再循环系统的系统。 再循环系统包括从压缩机延伸到进气口的压缩机排出空气管线。 压缩机排出空气管路构成为使压缩机排出气流流动，进气口构成为向压缩机供给空气流。 喷射器沿着压缩机和进气口之间的压缩机排出空气管线设置。 喷射器被配置为接收和混合压缩机排出空气流和涡轮排气流以形成第一混合物。

公开(公告)号：US20160265437A1

公开(公告)日：2016-09-15

申请号：US15158894

申请日：2016-05-19

Applicant: Masato YOSHINO ,  Hiroki FUJIWARA

Inventor： Masato YOSHINO ,  Hiroki FUJIWARA

IPC: F02C7/06 ,  F16C27/02 ,  F16C17/02

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).