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    REVERSE FLOW SINGLE SPOOL CORE GAS TURBINE ENGINE
    31.
    发明申请
    REVERSE FLOW SINGLE SPOOL CORE GAS TURBINE ENGINE 审中-公开
    反向流动单缸阀芯涡轮发动机

    公开(公告)号：US20160102634A1

    公开(公告)日：2016-04-14

    申请号：US14639164

    申请日：2015-03-05

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Daniel Bernard Kupratis

    IPC: F02K3/04 ,  F02C7/057 ,  F02K1/00 ,  F02C3/06

    CPC classification number: F02K3/04 ,  F01D13/003 ,  F01D13/006 ,  F02C3/06 ,  F02C7/36 ,  F02K1/52 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/323 ,  F05D2250/314 ,  F05D2260/4031

    Abstract: A bypass housing receives a fan and defines a front end. An airflow path delivers air into an inlet duct over a limited circumferential extent of the bypass housing. An airflow path passes across a low pressure compressor rotor. An airflow path passes through a core engine, which includes a high pressure compressor rotor, a combustor, and a high pressure turbine rotor. Products of combustion downstream of the high pressure turbine rotor pass into an intermediate duct and then across a low pressure turbine rotor. The low pressure turbine rotor is positioned closer to the front end of the engine than is the high pressure turbine rotor. The low pressure turbine rotor is positioned axially intermediate the low pressure compressor rotor and the fan. The low pressure turbine rotor drives both the fan and the low pressure turbine rotor. An aircraft is also disclosed.

    Abstract translation: 旁路外壳接收风扇并限定前端。 气流路径将空气输送到旁路壳体的有限圆周范围内的入口管道中。 气流通过低压压缩机转子。 气流路径通过核心发动机，其包括高压压缩机转子，燃烧器和高压涡轮转子。 高压涡轮转子下游的燃烧产物进入中间管道，然后穿过低压涡轮转子。 低压涡轮转子比高压涡轮转子更靠近发动机前端。 低压涡轮转子轴向位于低压压缩机转子和风扇之间。 低压涡轮转子驱动风扇和低压涡轮转子。 还披露了一架飞机。

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    34.
    发明申请
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 审中-公开
    齿轮涡轮发动机涡轮发动机结构

    公开(公告)号：US20150330302A1

    公开(公告)日：2015-11-19

    申请号：US14789300

    申请日：2015-07-01

    Applicant: United Technologies Corporation

    Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

    IPC: F02C3/107 ,  F02C7/06

    CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D9/02 ,  F01D9/065 ,  F02C3/04 ,  F02C3/107 ,  F02C3/36 ,  F02C7/06 ,  F02C9/18 ,  F02K1/78 ,  F02K3/04 ,  F02K3/06 ,  F02K3/072 ,  F04D27/009 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

    Abstract translation: 燃气涡轮发动机通常包括风扇部分，压缩机部分，燃烧器部分和涡轮部分。 可以使用诸如行星齿轮组件的减速装置来驱动风扇部分，使得风扇部分可以以不同于涡轮机部分的速度旋转，从而增加发动机的整体推进效率。 在这样的发动机结构中，由一个涡轮机部分驱动的轴为行星齿轮组件提供输入，该输入齿轮组件以不同于涡轮机部分的速度驱动风扇部分，使得涡轮部分和风扇部分可以更接近 最佳速度通过所述和所公开的燃气涡轮发动机的各种部件的公开特征的期望组合来提供增加的性能属性和性能。

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    35.
    发明申请
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 审中-公开

    公开(公告)号：US20150192070A1

    公开(公告)日：2015-07-09

    申请号：US14662459

    申请日：2015-03-19

    Applicant: United Technologies Corporation

    Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

    IPC: F02C7/32 ,  F02K3/02

    CPC classification number: F02C7/32 ,  F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/072 ,  F05D2240/12 ,  F05D2240/129 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    37.
    发明申请
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 审中-公开

    公开(公告)号：US20130192201A1

    公开(公告)日：2013-08-01

    申请号：US13645626

    申请日：2012-10-05

    Applicant: United Technologies Corporation

    Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

    IPC: F02K3/075

    CPC classification number: F02C7/06 ,  F02K3/06 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

    Augmented drive of compressors via differential and multistage turbine
    39.
    发明授权
    Augmented drive of compressors via differential and multistage turbine 有权

    公开(公告)号：US11421590B2

    公开(公告)日：2022-08-23

    申请号：US16656931

    申请日：2019-10-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan ,  Arthur M. Salve, Jr.

    IPC: F02C3/113 ,  F02C3/14 ,  F02C9/56 ,  F02K3/10 ,  F02C9/00

    Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.

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