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公开(公告)号：US20190154055A1
公开(公告)日：2019-05-23
申请号：US15819215
申请日：2017-11-21
Applicant: General Electric Company
Inventor： ASPI Rustom WADIA , Deepak Manohar Kamath , Daniel Waslo
Abstract: A turbofan engine comprising a compressor rotor, a plurality of main blades, the main blades are circumferentially mounted on the compressor rotor; a plurality of spinner blades, the spinner blades are circumferentially mounted on the compressor rotor, the spinner blades are located forward to the leading edge of the main blades; each spinner blade is circumferentially offset to a corresponding main blade.
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公开(公告)号：US10670037B2
公开(公告)日：2020-06-02
申请号：US15819215
申请日：2017-11-21
Applicant: General Electric Company
Inventor： Aspi Rustom Wadia , Deepak Manohar Kamath , Daniel Waslo
Abstract: A turbofan engine includes a compressor rotor, a plurality of main blades circumferentially mounted on the compressor rotor, and a plurality of spinner blades circumferentially mounted on the compressor rotor. Each of the spinner blades is located forward of a leading edge of a corresponding one of the main blades. Each of the spinner blades is circumferentially offset to the corresponding one of the main blades.
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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.
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公开(公告)号：US09932124B2
公开(公告)日：2018-04-03
申请号：US14654925
申请日：2013-11-26
Applicant: General Electric Company
CPC classification number: B64D37/30 , F02C3/22 , F02C6/08 , F02C7/224 , F02C7/236 , F02C9/40 , Y02T50/672
Abstract: A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, including a tank for storing cryogenic fuel, a supply line operably coupling the tank to the combustion chamber and a pump coupling the tank to the supply line to pump the cryogenic fuel at high pressure through the supply line where the pump is operably coupled to the compressor such that operation of the turbine engine drives the pump and a method for delivering fuel in a fuel system to a turbine engine.
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