-
公开(公告)号:US10415897B2
公开(公告)日:2019-09-17
申请号:US15037432
申请日:2014-11-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor: Thomas Kupiszewski , Mehdi Milani Baladi , John Andrew Kemme , Christopher Charles Glynn , Steven Douglas Johnson , Michael Jay Epstein
Abstract: A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flow to a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.
-
12.
公开(公告)号:US09656762B2
公开(公告)日:2017-05-23
申请号:US14651583
申请日:2013-11-26
Applicant: General Electric Company
Inventor: Deepak Manohar Kamath , Mehdi Milani Baladi , Sergei A. Jerebets , Robert Lawrence Mayer , Scott Chandler Morton , Alejandro Yatzail Perez Valadez
CPC classification number: B64D37/30 , B64D37/34 , F02C3/22 , F02C7/222 , F02C7/224 , F02C9/40 , F05D2260/207 , Y02T50/44 , Y02T50/672 , Y02T50/676
Abstract: A system for fluid temperature control and actuation control for an aircraft engine fueled by dual fuels. The system includes a first fuel system having a first fuel tank fluidly coupled to the engine, a second fuel system having a second fuel tank fluidly coupled to the engine, with the second fuel being different from the first fuel and having a different temperature than the first fuel, a fuel distribution unit (FDU) fluidly coupled to the first fuel tank of the first fuel system, and a fuel-to-fuel cooler (FFC) configured to transfer heat between the first fuel in the first fuel system and the second fuel in the second fuel system.
-
公开(公告)号:US20240328328A1
公开(公告)日:2024-10-03
申请号:US18740010
申请日:2024-06-11
Applicant: GE Avio S.r.l. , GENERAL ELECTRIC COMPANY
Inventor: Mehdi Milani Baladi , Paul Robert Gemin
IPC: F01D15/12
CPC classification number: F01D15/12 , F05D2220/32 , F05D2220/76 , F05D2260/4023
Abstract: A turbine engine with a turbine core that includes a compressor section having a compressor, a combustion section, a turbine section having a high pressure turbine and a low pressure turbine, and a nozzle section. A high speed shaft couples the high pressure turbine to the compressor. A first gearbox selectively coupling an output of an electric machine and the high speed shaft. A second gearbox couples an input/output of the electric machine and a low speed shaft, where the low speed shaft is coupled to the low pressure turbine.
-
公开(公告)号:US20190195128A1
公开(公告)日:2019-06-27
申请号:US16326783
申请日:2017-08-08
Applicant: General Electric Company
Inventor: Carlos Enrique Diaz , Alvaro Enrique Hernandez , Mehdi Milani Baladi , David William Kimball
CPC classification number: F02C7/042 , B60K11/08 , B60Y2200/50 , B60Y2200/51 , B64D27/10 , B64D27/16 , B64D29/00 , B64D33/08 , B64D2241/00 , F01D25/28 , F02C7/04 , F02C7/18 , F03G7/065 , F05D2220/323 , F05D2230/60 , F05D2270/05 , Y02T50/672 , Y02T50/675
Abstract: An air intake system includes an exterior housing for a vehicle, the exterior housing including an outer surface including a recessed portion defined therein. The recessed portion includes an angled bottom member having a first end and a second end that is coupled to the outer surface. The recessed portion further includes a first sidewall, a second sidewall opposing the first sidewall, and an inlet opening defined within the recessed portion. The inlet opening is bounded by the first sidewall, the second sidewall, and the second end, and the inlet opening is configured to receive a fluid stream therethrough. The air intake system further includes an actuation component coupled to the angled bottom member. The actuation component includes a shape memory alloy, and the actuation component is responsive to a change in a thermal condition and configured to move the second end, thereby regulating the inlet opening.
-
公开(公告)号:US10316696B2
公开(公告)日:2019-06-11
申请号:US14707938
申请日:2015-05-08
Applicant: General Electric Company
Inventor: Mehdi Milani Baladi , Abdus Shamim , Joseph Anthony Cotroneo
Abstract: A system includes a turbine with an expansion section configured to expand an exhaust flow in a downstream direction, such that the expansion section includes a plurality of stages and a diffuser section coupled downstream of the expansion section. The diffuser section receives the exhaust flow along an exhaust path and an energizing flow along a wall, and the diffuser section includes the wall comprising an inner surface, so the wall is disposed about the exhaust path, and an energizing port disposed in the wall at or downstream of a last stage of the plurality of stages of the expansion section. The energizing port is configured to direct the energizing flow along the inner surface of the wall to energize a boundary layer along the wall, and a first pressure of the energizing flow is greater than a second pressure of the exhaust flow at the energizing port.
-
16.
公开(公告)号:US20160326960A1
公开(公告)日:2016-11-10
申请号:US14707938
申请日:2015-05-08
Applicant: General Electric Company
Inventor: Mehdi Milani Baladi , Abdus Shamim , Joseph Anthony Cotroneo
CPC classification number: F01D25/305 , F01D11/24 , F01D25/08 , F01D25/12 , F01D25/14 , F01D25/30 , F02C6/18 , F02C7/12 , F02C7/125 , F02C9/18 , F05D2260/2322 , F05D2270/17 , F05D2270/173 , Y02T50/671 , Y02T50/676
Abstract: A system includes a turbine with an expansion section configured to expand an exhaust flow in a downstream direction, such that the expansion section includes a plurality of stages and a diffuser section coupled downstream of the expansion section. The diffuser section receives the exhaust flow along an exhaust path and an energizing flow along a wall, and the diffuser section includes the wall comprising an inner surface, so the wall is disposed about the exhaust path, and an energizing port disposed in the wall at or downstream of a last stage of the plurality of stages of the expansion section. The energizing port is configured to direct the energizing flow along the inner surface of the wall to energize a boundary layer along the wall, and a first pressure of the energizing flow is greater than a second pressure of the exhaust flow at the energizing port.
Abstract translation: 一种系统包括具有膨胀部分的涡轮机,该膨胀部分构造成在下游方向上扩张排气流,使得膨胀部分包括多个级,以及连接在膨胀部分下游的扩散部分。 扩散器部分接收沿着排气通道的排气流和沿壁的通电流,并且扩散器部分包括包括内表面的壁,因此壁围绕排气路径设置,并且通电端口设置在壁中 或扩展部分的多个阶段的最后阶段的下游。 通电端口被构造成沿着壁的内表面引导通电流,以激励沿着壁的边界层,并且通电流的第一压力大于在通电端口处的排气流的第二压力。
-
公开(公告)号:US20140271168A1
公开(公告)日:2014-09-18
申请号:US13798614
申请日:2013-03-13
Applicant: General Electric Company
Inventor: Fernando Lopez-Parra , Balakrishnan Ponnuraj , Przemyslaw Drezek , Mehdi Milani Baladi , Ravinder Yerram , Donald Gordon Laing
IPC: F01D25/30
CPC classification number: F01D25/30
Abstract: The present application provides a radial diffuser exhaust system for use with a gas turbine engine. The radial diffuser exhaust system may include a radial diffuser positioned within an asymmetric exhaust collector. The asymmetric exhaust collector may include a closed end chamber and an exhaust end chamber. The closed end chamber may have a first size, the exhaust end chamber may have a second size, and the first size may be smaller than the second size.
Abstract translation: 本申请提供了一种与燃气涡轮发动机一起使用的径向扩散器排气系统。 径向扩散器排气系统可以包括位于不对称排气收集器内的径向扩散器。 不对称排气收集器可以包括封闭端室和排气端室。 封闭端室可以具有第一尺寸,排气端室可以具有第二尺寸,并且第一尺寸可以小于第二尺寸。
-
公开(公告)号:US11945573B2
公开(公告)日:2024-04-02
申请号:US17529556
申请日:2021-11-18
Applicant: General Electric Company , GE Avio S.r.l.
Inventor: Mehdi Milani Baladi , Randy M Vondrell
CPC classification number: B64C17/06 , B64C29/0033 , B64D27/14 , B64D27/24 , B64D31/02 , B64D2027/026
Abstract: A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.
-
公开(公告)号:US11300368B2
公开(公告)日:2022-04-12
申请号:US16532846
申请日:2019-08-06
Applicant: General Electric Company
Inventor: Thomas Kupiszewski , Christopher Charles Glynn , Steven Douglas Johnson , John Andrew Kemme , Mehdi Milani Baladi , Michael Epstein
Abstract: A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flow 46 to a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.
-
公开(公告)号:US09957900B2
公开(公告)日:2018-05-01
申请号:US14709343
申请日:2015-05-11
Applicant: General Electric Company
Inventor: Mehdi Milani Baladi , Edward Michael Yanosik, Jr. , Richard Bradford Hook, Jr. , Scott Edward Farley , Gordon Jeffery Follin
CPC classification number: F02C9/18 , F01D5/145 , F01D5/148 , F01D17/14 , F02C3/04 , F02C9/20 , F02K1/30 , F05D2220/32 , F05D2260/16 , F05D2260/202 , F15D1/008 , F15D1/025 , Y02T50/673 , Y02T50/675
Abstract: One embodiment of the present discloses includes a system. The system includes a turbine and a fluid supply system. The turbine includes a main flow path, a plurality of turbine blades disposed along the main flow path, at least one flow control area disposed along the main flow path, and at least one fluid injection port fluidly coupled to the main flow path. The fluid supply system is fluidly coupled to the at least one fluid injection port, wherein the fluid supply system is configured to supply a fluid to the at least one fluid injection port to adjust an effective area of the at least one flow control area.
-
-
-
-
-
-
-
-
-