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    CONCENTRIC SHAFTS DRIVING ADJACENT FANS FOR AIRCRAFT PROPULSION
    43.
    发明公开
    CONCENTRIC SHAFTS DRIVING ADJACENT FANS FOR AIRCRAFT PROPULSION 审中-公开

    公开(公告)号：EP3333373A1

    公开(公告)日：2018-06-13

    申请号：EP17206222.6

    申请日：2017-12-08

    Applicant: United Technologies Corporation

    Inventor： CHANDLER, Jesse M. ,  SUCIU, Gabriel L.

    IPC: F01D13/00 ,  B64D35/04 ,  B64D35/08 ,  F02K3/062 ,  F02C3/107 ,  B64D27/10

    CPC classification number: F02K3/062 ,  B64D27/10 ,  B64D35/04 ,  B64D35/08 ,  F01D13/003 ,  F02C3/107 ,  F05D2250/312

    Abstract: A propulsion system for an aircraft has at least two fans (22, 24; 122, 124; 208, 210), each fan (22...210) having a fan drive shaft (56; 156). A turboshaft gas turbine engine (26, 28; 126, 128; 202, 204) drives each of the at least two fans (22...210), and drive an output shaft (36; 136) which drives a gear (38; 138) to, in turn, engage for driving a gear (40; 140) on a first intermediate shaft (41, 42; 141; 206, 207) extending from the turboshaft gas turbine engine (26...204) in a rearward direction toward an intermediate fan drive shaft (50; 150). The intermediate fan drive shaft (50; 150) drives the fan drive shaft (56; 156), and the first intermediate shafts (41...207) extend over a distance that is greater in an axial dimension defined between the turboshaft gas turbine engine (26...204) and the fan (22...210) than in a width dimension defined between the at least two fans (22...210). The first intermediate shafts (41...207) are concentric.

    GAS GENERATOR BIFURCATING EXHAUST DUCT TO FREE TURBINE
    44.
    发明公开
    GAS GENERATOR BIFURCATING EXHAUST DUCT TO FREE TURBINE 审中-公开
    气体发生器分流排气管至涡轮机

    公开(公告)号：EP3284943A1

    公开(公告)日：2018-02-21

    申请号：EP17186611.4

    申请日：2017-08-17

    Applicant: United Technologies Corporation

    Inventor： CHANDLER, Jesse M. ,  SUCIU, Gabriel L.

    IPC: F02K3/062 ,  F02C3/10

    CPC classification number: F02C3/10 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04 ,  F01D25/30 ,  F02C7/36 ,  F02K3/062 ,  F02K3/12 ,  F05D2220/32 ,  F05D2250/314 ,  F05D2260/40311

    Abstract: A gas turbine engine (15) for an aircraft (10) includes a core engine assembly (16A, 16B) including a compressor section (20A, 20B) communicating air to a combustor section (22) where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section (24A, 24B). The turbine section (24A, 24B) is coupled to drive the compressor section (20A, 20B). A free turbine (26; 46A, 46B) is configured to be driven by gas flow from the core engine assembly (16A, 16B). A propulsor section (18) is aft of the core engine assembly (16A, 16B) and is driven by the free turbine (26; 46A, 46B). An exhaust duct (32) routes exhaust gases from the core engine assembly (16A, 16B) to the free turbine (26; 46A, 46B). The free turbine (26; 46A, 46B) is disposed aft of the propulsor section (18) and the exhaust duct (32) includes an outlet (25) aft of the propulsor section (18) communicating gas flow to drive the free turbine (26; 46A, 46B). An aircraft (10) is also disclosed.

    Abstract translation: 一种用于飞行器（10）的燃气涡轮发动机（15），包括：包括将空气传送到燃烧器部分（22）的压缩机部分（20A，20B）的核心发动机组件（16A，16B），其中空气与燃料混合并被点燃 以产生通过涡轮段（24A，24B）膨胀的高能气流。 涡轮部分（24A，24B）联接以驱动压缩机部分（20A，20B）。 自由涡轮机（26; 46A，46B）构造成由来自核心发动机组件（16A，16B）的气流驱动。 推进器部分（18）位于核心发动机组件（16A，16B）的后面并由自由涡轮机（26; 46A，46B）驱动。 排气管道（32）将来自核心发动机组件（16A，16B）的排气引导至自由涡轮机（26; 46A，46B）。 自由涡轮机（26; 46A，46B）设置在推进器部分（18）的后面，并且排气管道（32）包括推进器部分（18）的后部的出口（25），该出口连通气流以驱动自由涡轮机 26; 46A，46B）。 还公开了一种飞机（10）。

    EXHAUST DUCT FOR TURBINE FORWARD OF FAN
    45.
    发明公开
    EXHAUST DUCT FOR TURBINE FORWARD OF FAN 审中-公开
    用于风扇前方的涡轮排气管

    公开(公告)号：EP3282117A1

    公开(公告)日：2018-02-14

    申请号：EP17185189.2

    申请日：2017-08-07

    Applicant: United Technologies Corporation

    Inventor： LORD, Wesley K. ,  CHANDLER, Jesse M. ,  SUCIU, Gabriel L.

    IPC: F02K3/062 ,  B64D33/04 ,  B64D27/14 ,  B64D35/04

    CPC classification number: F02K3/00 ,  B64D27/14 ,  B64D33/02 ,  B64D33/04 ,  B64D35/04 ,  F02K1/52 ,  F02K3/062 ,  F05D2250/312

    Abstract: A gas turbine engine (10) includes a core engine (16) including a compressor section (20) communicating air to a combustor section (22) where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section (24). The turbine section (24) is coupled to drive the compressor section (20). A propulsor (18) aft of the core engine (16) is driven by the turbine section (24). An exhaust duct (42) routes exhaust gases around the propulsor (18). The exhaust duct (42) includes an inlet (46) forward of the propulsor (18), an outlet (40) aft of the turbine section (24) and a passageway between the inlet and the outlet.

    Abstract translation: 燃气涡轮发动机（10）包括核心发动机（16），该核心发动机包括将空气传送到燃烧器部分（22）的压缩机部分（20），在燃烧器部分（22）中，空气与燃料混合并被点燃以产生膨胀的高能气体流 通过涡轮段（24）。 涡轮部分（24）被联接以驱动压缩机部分（20）。 涡轮部分（24）驱动核心发动机（16）后面的推进器（18）。 排气管（42）在推进器（18）周围排出废气。 排气管道（42）包括推进器（18）前方的入口（46），涡轮部分（24）后方的出口（40）以及入口和出口之间的通道。

    COMBINED DRIVE FOR COOLING AIR USING COOLING COMPRESSOR AND AIRCRAFT AIR SUPPLY PUMP
    47.
    发明公开
    COMBINED DRIVE FOR COOLING AIR USING COOLING COMPRESSOR AND AIRCRAFT AIR SUPPLY PUMP 审中-公开
    用冷却压缩机和飞机空气供给泵冷却空气的组合驱动器

    公开(公告)号：EP3239478A1

    公开(公告)日：2017-11-01

    申请号：EP17168271.9

    申请日：2017-04-26

    Applicant: United Technologies Corporation

    Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D. ,  CHANDLER, Jesse M.

    IPC: F01D25/00 ,  F02C6/08 ,  F02C7/18 ,  F02C7/32 ,  F02C7/36

    CPC classification number: F02C7/185 ,  F02C3/04 ,  F02C6/08 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/32 ,  Y02T50/675

    Abstract: A gas turbine engine (100) comprises a main compressor section having a high pressure compressor (108) with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine (117). A first tap (110) taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger (112) and then to a cooling compressor (114). The cooling compressor (114) compresses air downstream of the heat exchanger (112), and delivers air into the high pressure turbine (117). A second tap (208) taps air from the compressor section, passes the air across a cabin air pump (212), and delivers air from the cabin air pump (212) for use on an aircraft receiving the gas turbine engine (100). The cooling compressor (114) including a rotor, and the cabin air pump (212) including a rotor, and a drive (300) driven with the turbine section in turn drives both the cooling compressor rotor and the cabin air supply rotor.

    Abstract translation: 燃气涡轮发动机（100）包括主压缩机部分和更多的上游位置，主压缩机部分具有带有下游排气口的高压压缩机（108）。 涡轮机部分具有高压涡轮机（117）。 第一龙头（110）从压缩机部分的更上游位置中的至少一个中抽取空气，将抽取的空气通过热交换器（112），然后传送至冷却压缩机（114）。 冷却压缩机（114）压缩热交换器（112）下游的空气，并将空气输送到高压涡轮机（117）中。 第二龙头208从压缩机部分抽出空气，使空气穿过机舱空气泵212，并且从机舱空气泵212输送空气以用于接收燃气涡轮发动机100的飞机上。 包括转子的冷却压缩机（114）和包括转子的机舱空气泵（212）以及由该涡轮机部分驱动的驱动器（300）依次驱动冷却压缩机转子和机舱空气供给转子。

    INTERCOOLED COOLING AIR WITH AUXILIARY COMPRESSOR CONTROL
    49.
    发明公开
    INTERCOOLED COOLING AIR WITH AUXILIARY COMPRESSOR CONTROL 审中-公开
    ZWISCHENGEKÜHLTEKÜHLLUFTMIT HILFSKOMPRESSORSTEUERUNG

    公开(公告)号：EP3109437A1

    公开(公告)日：2016-12-28

    申请号：EP16175552.5

    申请日：2016-06-21

    Applicant: United Technologies Corporation

    Inventor： MERRY, Brian D. ,  SUCIU, Gabriel L. ,  CHANDLER, Jesse M. ,  ROBERGE, Gary D. ,  STAUBACH, Joseph Brent

    IPC: F02C6/08 ,  F02C7/12 ,  F02C9/18

    CPC classification number: F02C6/08 ,  F02C7/12 ,  F02C9/18 ,  Y02T50/675

    Abstract: A gas turbine engine comprises a main compressor section (24) having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section (28) has a high pressure turbine (117). A tap (110) taps air from at least one of the more upstream locations in the compressor section, passing the tapped air through a heat exchanger (112) and then to a cooling compressor (114), which compresses air downstream of the heat exchanger (112), and delivers air into the high pressure turbine (117). The cooling compressor (114) rotates at a speed proportional to a speed of at least one rotor in the turbine section (28). The cooling compressor (114) is allowed to rotate at a speed that is not proportional to a speed of the at least one rotor under certain conditions. An intercooling system for a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括具有下游排出口的高压压缩机和更多上游位置的主压缩机部分（24）。 涡轮机部分（28）具有高压涡轮机（117）。 抽头（110）从压缩机部分中的上游位置中的至少一个抽吸空气，使抽头的空气通过热交换器（112），然后到达冷却压缩机（114），该冷却压缩机压缩热交换器 （112），并且将空气输送到高压涡轮机（117）中。 冷却压缩机（114）以与涡轮部（28）中的至少一个转子的速度成比例的速度旋转。 允许冷却压缩机（114）在一定条件下以与至少一个转子的速度成比例的速度旋转。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

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