公开(公告)号：US20060230762A1

公开(公告)日：2006-10-19

申请号：US10542340

申请日：2004-01-19

Applicant: Stellan Hamrin

Inventor： Stellan Hamrin

IPC: F02C1/04

CPC classification number: F02C7/141 ,  B01D53/22 ,  F02C9/18 ,  F05D2270/303 ,  F23L2900/07001 ,  Y02E20/322 ,  Y02T50/675

Abstract: A method for producing, on an SiC substrate, SiC homoepitaxial layers of the same polytype as the substrate. The layers are grown on a surface of the SiC substrate, wherein the surface is inclined relative to the (0001) basal plane at an angle higher than 0.1 degree but less than 1 degree. An homoepitaxial growth is started by forming a boundary layer with a thickness up to 1 μm.

Abstract translation: 在SiC衬底上制造与衬底相同的多型式的SiC同质外延层的方法。 这些层在SiC衬底的表面上生长，其中表面相对于（0001）基面以高于0.1度但小于1度的角度倾斜。 通过形成厚度达1μm的边界层开始同质外延生长。

公开(公告)号：US06824351B2

公开(公告)日：2004-11-30

申请号：US10275109

申请日：2002-11-01

Applicant: Hans-Joachim Endries ,  Udo Gande ,  Volker Taubitz ,  Michael Wechsung

Inventor： Hans-Joachim Endries ,  Udo Gande ,  Volker Taubitz ,  Michael Wechsung

IPC: F01D2512

CPC classification number: F02C7/141 ,  F01D25/12 ,  F05D2220/31 ,  F05D2260/20 ,  F05D2260/213 ,  F05D2260/2322

Abstract: A method and a device are for cooling the inflow area of the shaft of a steam turbine. According to the method and device, a partial mass flow m1 is branched off upstream of a feed device that supplies the steam to the team turbine. The partial mass flow is cooled and then guided to the feed device, from where it is supplied to the steam turbine together with the remaining mass flow m2. The method and device allow for a simplified control and design of the turbine.

Abstract translation: 一种方法和装置用于冷却蒸汽轮机的轴的流入区域。 根据该方法和装置，部分质量流量m1在向蒸汽轮机供给蒸汽的进料装置的上游分支。 部分质量流量被冷却，然后被引导到进料装置，从其被供应到蒸汽涡轮机以及剩余质量流量m2。 该方法和装置允许简化涡轮机的控制和设计。

公开(公告)号：US4228659A

公开(公告)日：1980-10-21

申请号：US908155

申请日：1978-05-22

Applicant: Frank E. Lowther

Inventor： Frank E. Lowther

IPC: F02C1/10 ,  F02C7/141 ,  F01K25/00

CPC classification number: F02C7/141 ,  F02C1/10 ,  Y02T50/675

Abstract: A constant pressure, Brayton cycle gas turbine method and apparatus including a combustion chamber and a turbine and using a hot-cool operating cycle comprising a hot phase alternating with cool phase. Gas is continuously fed to the combustion chamber and from the combustion chamber to the turbine. During the hot phase all of the gas fed to the turbine is hot. The gas temperature during the hot phase is higher than the turbine could withstand in a continuous burn mode. However, the time period of the hot phase is less than the time it would take for the turbine blades to "soak" to the high temperature of the hot gas. This provides a high combustion temperature and high efficiency at all times, eliminating the part-load efficiency loss of the prior art, and also eliminating the need for high temperature materials as well as the prior art compressor requirements for large amounts of air. The gas turbine can be of the closed cycle or open cycle type. Applications include, for example, automobiles, air craft, railroad engines, central station power and golf carts.

Abstract translation: 一种恒定压力的布雷顿循环燃气轮机方法和装置，包括燃烧室和涡轮，并且使用包括与冷相交替的热相的热冷运行循环。 气体被连续地供给到燃烧室并且从燃烧室到达涡轮机。 在热阶段期间，所有送入涡轮机的气体都是热的。 热段期间的气体温度高于涡轮机在连续燃烧模式下可承受的温度。 然而，热相的时间段小于涡轮叶片“浸泡”到热气体的高温所需的时间。 这始终提供高燃烧温度和高效率，消除了现有技术的部分负载效率损失，并且还消除了对高温材料的需要以及现有技术对大量空气的压缩机要求。 燃气轮机可以是封闭循环或开式循环型。 应用包括例如汽车，飞机，铁路发动机，中央车站电源和高尔夫球车。

公开(公告)号：US3038308A

公开(公告)日：1962-06-12

申请号：US59799156

申请日：1956-07-16

Applicant: FULLER NANCY W N ,  NATIONAL BANK THE PHILADELPHIA

Inventor： FULLER NANCY W N ,  NATIONAL BANK THE PHILADELPHIA

IPC: F01K21/04 ,  F02C7/141

CPC classification number: F02C7/141 ,  F01K21/047 ,  Y02T50/675

公开(公告)号：US2869323A

公开(公告)日：1959-01-20

申请号：US63222057

申请日：1957-01-02

Applicant: GEN ELECTRIC

Inventor： NEST FRANCIS H VAN

IPC: F01K21/04 ,  F02C7/141

CPC classification number: F02C7/141 ,  F01K21/047

公开(公告)号：US2115338A

公开(公告)日：1938-04-26

申请号：US70201433

申请日：1933-12-12

Applicant: MILO AB

Inventor： ALF LYSHOLM

IPC: F02C3/36 ,  F02C7/141

CPC classification number: F02C3/36 ,  F02C7/141

公开(公告)号：US20240360788A1

公开(公告)日：2024-10-31

申请号：US18771005

申请日：2024-07-12

Applicant: RTX CORPORATION

Inventor： Brandon M. Evans ,  Neil J. Terwilliger

IPC: F02C3/30 ,  F02C1/10 ,  F02C3/22 ,  F02C6/18 ,  F02C7/141

CPC classification number: F02C3/30 ,  F02C1/10 ,  F02C3/22 ,  F02C6/18 ,  F02C7/141 ,  F05D2220/323 ,  F05D2260/213

Abstract: An aircraft propulsion system includes a core engine and a bottoming cycle where a working fluid is circulated within a closed circuit. A first heat exchanger is used to transfer heat from a portion of thermal energy from the exhaust gas flow to working fluid of the bottoming cycle. A fuel/working fluid heat exchanger provides the cryogenic fuel to cool the working fluid exhausted from a bottoming turbine and before a bottoming compressor.

公开(公告)号：US20240309813A1

公开(公告)日：2024-09-19

申请号：US18121377

申请日：2023-03-14

Applicant: Raytheon Technologies Corporation

Inventor： Stephen K. Kramer ,  Lance L. Smith ,  Gregory Boardman ,  Zhongtao Dai

IPC: F02C7/141 ,  F02C7/16

CPC classification number: F02C7/141 ,  F02C7/16 ,  F05D2240/12 ,  F05D2260/212 ,  F05D2260/2322 ,  F05D2270/16

Abstract: An assembly is provided for a turbine engine. This assembly includes a turbine vane array and a cooling system. The turbine vane array includes an inner platform, an outer platform and a plurality of turbine vanes extending between and connected to the inner platform and the outer platform. The turbine vanes include a first turbine vane, and the first turbine vane includes a first passage and a second passage. The cooling system is configured to direct a first fluid into the first passage and a second fluid into the second passage. The first fluid includes air and steam during a first mode. The second fluid includes the air without the steam during the first mode.

公开(公告)号：US12085020B1

公开(公告)日：2024-09-10

申请号：US18238636

申请日：2023-08-28

Applicant: Air Products and Chemicals, Inc.

Inventor： Gregory W. Henzler ,  Paul D. Altpeter ,  Ghassan Altimany ,  Tito Paratico

IPC: F02C7/052 ,  B01D46/00 ,  B01D46/42 ,  B01D46/62 ,  F02C7/141 ,  F02C7/224 ,  F23R3/04 ,  F23R3/30

CPC classification number: F02C7/052 ,  B01D46/0031 ,  B01D46/4263 ,  B01D46/62 ,  F02C7/141 ,  F02C7/224 ,  F23R3/04 ,  F23R3/30 ,  B01D2279/60 ,  F05D2260/20

Abstract: An apparatus and process can be configured for filtering and cooling air to be fed to a gas turbine while also vaporizing at least a portion of fuel to be fed to the gas turbine. Intake air can be passed through a filter house for filtration. While passing through the filtration house, a liquid fuel can be passed through the filter house to be vaporized or partially vaporized therein via heat exchange with the air passing through the filter house, which can also cool the air as it is passing through the filter house. Filtered, cooled air can be output from the filter house for feeding to a gas turbine as an oxidant while the at least partially vaporized fuel can also be output from the filter house for feeding to the gas turbine for being combusted therein.

公开(公告)号：US12071889B2

公开(公告)日：2024-08-27

申请号：US17713649

申请日：2022-04-05

Applicant: General Electric Company ,  General Electric Deutschland Holding GmbH ,  GE Avio Srl

Inventor： Paul Hadley Vitt ,  Lyle Douglas Dailey ,  Matteo Renato Usseglio ,  Andreas Peters ,  Jonathan Ong

IPC: F02C3/06 ,  F02C3/067 ,  F02C7/14 ,  F02C7/141 ,  F02C7/36

CPC classification number: F02C3/067 ,  F02C7/141 ,  F02C7/36 ,  F05D2220/60 ,  F05D2260/213 ,  F05D2260/40311

Abstract: A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.