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    Supercritical CO2 cycle for gas turbine engines using powered cooling flow
    1.
    发明授权
    Supercritical CO2 cycle for gas turbine engines using powered cooling flow 有权

    公开(公告)号：US11428162B2

    公开(公告)日：2022-08-30

    申请号：US16746284

    申请日：2020-01-17

    Applicant: United Technologies Corporation

    Inventor： Joseph B. Staubach ,  Amanda J. L. Boucher

    IPC: F02C7/141 ,  F02C6/18 ,  F01K25/10

    Abstract: Gas turbine engines are described. The gas turbine engines includes a compressor section, a combustor section, a turbine section, and a nozzle section. The compressor section, the combustor section, the turbine section, and the nozzle section define a core flow path that expels through the nozzle section. A cooling duct is provided that is separate from the core flow path. A waste heat recovery system is arranged with a heat rejection heat exchanger arranged within the cooling duct and a blower is arranged within the cooling duct and configured to generate a pressure drop across the heat rejection heat exchanger.

    HYDROGEN PROPULSION SYSTEMS FOR AIRCRAFT
    2.
    发明申请
    HYDROGEN PROPULSION SYSTEMS FOR AIRCRAFT 有权

    公开(公告)号：US20210300575A1

    公开(公告)日：2021-09-30

    申请号：US16832477

    申请日：2020-03-27

    Applicant: United Technologies Corporation

    Inventor： Joseph B. Staubach ,  Amanda J. L. Boucher

    IPC: B64D27/12 ,  B64D41/00 ,  B64D13/08

    Abstract: Aircraft propulsion systems and aircraft having such propulsion systems are described. The aircraft propulsion systems include a fan, a motor operably connected to the fan by a drive shaft, and an aircraft power generation system operably coupled to the motor to drive rotation of the fan through the drive shaft, wherein the aircraft power generation system comprises a fuel cell configured to generate at least 1 MW of electrical power.

    TURBINE SECTION OF HIGH BYPASS TURBOFAN
    5.
    发明申请
    TURBINE SECTION OF HIGH BYPASS TURBOFAN 审中-公开

    公开(公告)号：US20190017446A1

    公开(公告)日：2019-01-17

    申请号：US16025038

    申请日：2018-07-02

    Applicant: United Technologies Corporation

    Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: F02C7/36 ,  F02K3/06 ,  F02C9/18 ,  F01D11/12 ,  F01D5/06 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D19/02 ,  F02K3/075 ,  F02C3/107

    Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including a circumferential array of fan blades, a compressor in fluid communication with the fan, the compressor including a first compressor section and a second compressor, the second compressor section including a second compressor section inlet with a second compressor section inlet annulus area, a fan duct including a fan duct annulus area outboard of the second compressor section inlet, a shaft assembly having a first portion and a second portion, a turbine in fluid communication with the combustor, the turbine having a first turbine section coupled to the first portion of the shaft assembly to drive the first compressor section, and a second turbine section coupled to the second portion of the shaft assembly to drive the fan, an epicyclic transmission coupled to the fan and rotatable by the second turbine section through the second portion of the shaft assembly to allow the second turbine to turn faster than the fan, wherein the second turbine section includes a maximum gas path radius and the fan blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.6.

    TEMPERATURE-MODULATED RECUPERATED GAS TURBINE ENGINE
    6.
    发明申请
    TEMPERATURE-MODULATED RECUPERATED GAS TURBINE ENGINE 审中-公开
    温度调节式燃气涡轮发动机

    公开(公告)号：US20160369695A1

    公开(公告)日：2016-12-22

    申请号：US14740636

    申请日：2015-06-16

    Applicant: United Technologies Corporation

    Inventor： Jeffrey F. Perlak ,  Joseph B. Staubach ,  Frederick M. Schwarz ,  James D. Hill

    IPC: F02C7/10 ,  F02C3/04 ,  F02C9/18

    CPC classification number: F02C7/10 ,  F02C3/04 ,  F02C7/08 ,  F02C9/18 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2270/112 ,  F05D2270/3032 ,  Y02T50/676

    Abstract: A recuperated gas turbine engine includes an engine core that has a compressor section, a combustor section, and a turbine section. An exhaust duct is located downstream of the turbine section for receiving a hot turbine exhaust stream from the turbine section. The exhaust duct includes a heat exchanger and a temperature-control module upstream of the heat exchanger. A compressor bleed line leads from the compressor section into the heat exchanger and a compressor return line leads from the heat exchanger into the engine core upstream of the combustor section. The compressor bleed line is operable to selectively feed compressed air to the heat exchanger, and the temperature-control module is operable to selectively modulate at least one of temperature and flow of the hot turbine exhaust stream with respect to the heat exchanger.

    Abstract translation: 复原燃气涡轮发动机包括具有压缩机部分，燃烧器部分和涡轮部分的发动机芯。 排气管道位于涡轮机部分的下游，用于从涡轮机部分接收热涡轮机废气流。 排气管道包括在热交换器上游的热交换器和温度控制模块。 压缩机排气管路从压缩机部分引入热交换器，并且压缩机返回管线从热交换器引导到燃烧器部分上游的发动机芯。 压缩机排气管线可操作以选择性地将压缩空气供给到热交换器，并且温度控制模块可操作以选择性地调节热涡轮机废气流相对于热交换器的温度和流量中的至少一个。

    Hydrogen propulsion systems for aircraft
    8.
    发明授权
    Hydrogen propulsion systems for aircraft 有权

    公开(公告)号：US11511872B2

    公开(公告)日：2022-11-29

    申请号：US16832477

    申请日：2020-03-27

    Applicant: United Technologies Corporation

    Inventor： Joseph B. Staubach ,  Amanda J. L. Boucher

    IPC: B64D27/12 ,  B64D13/08 ,  B64D41/00

    Abstract: Aircraft propulsion systems and aircraft having such propulsion systems are described. The aircraft propulsion systems include a fan, a motor operably connected to the fan by a drive shaft, and an aircraft power generation system operably coupled to the motor to drive rotation of the fan through the drive shaft, wherein the aircraft power generation system comprises a fuel cell configured to generate at least 1 MW of electrical power.

    Gas turbine engine heat exchanger for annular flowpaths
    10.
    发明授权
    Gas turbine engine heat exchanger for annular flowpaths 有权

    公开(公告)号：US11378341B2

    公开(公告)日：2022-07-05

    申请号：US16733646

    申请日：2020-01-03

    Applicant: United Technologies Corporation

    Inventor： Joseph B. Staubach ,  Amanda Jean Boucher ,  Jesse M. Chandler

    IPC: F28D7/04 ,  F01K25/10 ,  F02C7/16 ,  F01K23/06 ,  F02C1/05 ,  F28D21/00

    Abstract: A heat exchanger has arcuate inlet and outlet manifolds and a plurality of tube banks, each tube bank coupling one of the inlet manifold outlets to an associated one of the outlet manifold inlets. Each tube bank partially nests with one or more others of the tube banks and has: a first header coupled to the associated inlet manifold outlet and the associated the outlet manifold inlet; a second header; and a plurality of tube bundles each having a first end coupled to the associated first header and a second end coupled to the associated second header. A flowpath from the each inlet manifold outlet passes sequentially through flowpath legs formed by each of the tube bundles in the associated tube bank to exit the tube bank to the associated outlet manifold inlet.

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