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121.发明申请Modifying a Gas Turbine Engine to Use a High Pressure Compressor as a Low Pressure Compressor 审中-公开修改燃气轮机使用高压压缩机作为低压压缩机公开(公告)号：US20160208689A1
公开(公告)日：2016-07-21
申请号：US14598269
申请日：2015-01-16
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Wesley K. Lord , Brian D. Merry
IPC: F02C3/10
CPC classification number: F02C3/06 , F05D2230/80
Abstract: A method comprises the steps of modifying an existing engine which includes a high pressure compressor driven by a high pressure turbine and a low pressure turbine to drive a low pressure compressor. The modifying step includes utilizing the high pressure compressor as a low pressure compressor in a modified gas turbine engine, and designing and incorporating a new high pressure compressor downstream of the low pressure compressor section in the modified engine, such that a portion of the design of the existing engine is utilized in the modified engine. A gas turbine engine is also disclosed.
Abstract translation: 一种方法包括以下步骤：修改现有的发动机，其包括由高压涡轮机和低压涡轮机驱动的高压压缩机，以驱动低压压缩机。 修改步骤包括在改性燃气涡轮发动机中利用高压压缩机作为低压压缩机，以及在改进的发动机中设计和并入低压压缩机部分下游的新的高压压缩机，使得设计的一部分 现有的发动机用于改进的发动机。 还公开了一种燃气涡轮发动机。
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公开(公告)号：US20160024957A1
公开(公告)日：2016-01-28
申请号：US14872405
申请日：2015-10-01
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson
CPC classification number: F01D25/28 , B64D27/26 , B64D2027/264 , B64D2027/266 , F01D1/02 , F01D5/02 , F01D5/06 , F01D9/02 , F01D15/12 , F01D17/105 , F01D17/14 , F01D17/16 , F01D25/162 , F01D25/24 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2230/60 , F05D2240/128 , F05D2240/24 , F05D2240/50 , F05D2260/4031 , F05D2260/40311
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, a first compressor section including three (3) or more stages, a second compressor section including between eight (8) and thirteen (13) stages, and a first turbine section operable for driving the first compressor section, the first turbine section including between three (3) and six (6) stages, a second turbine section operable for driving the second compressor section, and a gear train defined along an engine centerline axis. One of the first turbine section and the second turbine section is operable to drive the fan section through the gear train.
Abstract translation: 根据本公开的示例的燃气涡轮发动机包括除了别的以外的风扇部分，包括三（3）或更多级的第一压缩机部分，包括八（8）至十三（13） 以及可操作以驱动第一压缩机部分的第一涡轮机部分，第一涡轮部分包括三（3）和六（6）级，第二涡轮部分可操作以驱动第二压缩机部分，以及沿着 发动机中心轴。 第一涡轮部分和第二涡轮部分中的一个可操作以通过齿轮系驱动风扇部分。
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公开(公告)号：US20150377142A1
公开(公告)日：2015-12-31
申请号：US14767477
申请日：2014-02-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan , Gabriel L. Suciu , Brian D. Merry
CPC classification number: F02C7/275 , F01D19/00 , F02C3/107 , F02C7/36 , F05D2260/40 , F05D2260/403 , F05D2260/85
Abstract: A gas turbine engine comprises a first compressor, a second compressor, a starter generator and a clutch. The starter generator is coupled to the first compressor. The clutch selectively couples the second compressor and the first compressor. The clutch is disposed between a first shaft and a second shaft to engage the first shaft with the second shaft at rest. A flyweight system is engaged with the clutch mechanism to permit freewheeling of the first shaft relative to the second shaft when subject to rotational motion beyond a threshold speed. A method for starting a gas turbine engine comprises engaging a low pressure compressor with a high pressure compressor utilizing a clutch, rotating the low pressure compressor and the high pressure compressor utilizing a starter generator coupled to the low pressure compressor, igniting the gas turbine engine, and disengaging the clutch at an operational speed of the gas turbine engine.
Abstract translation: 燃气涡轮发动机包括第一压缩机，第二压缩机，起动发电机和离合器。 起动发电机联接到第一压缩机。 离合器选择性地联接第二压缩机和第一压缩机。 离合器设置在第一轴和第二轴之间，以使第一轴与静止的第二轴接合。 飞行重量系统与离合器机构接合以允许当经受超过阈值速度的旋转运动时第一轴相对于第二轴的续流。 一种用于启动燃气涡轮发动机的方法包括使用离合器将低压压缩机与高压压缩机接合，利用联接到低压压缩机的启动发电机旋转低压压缩机和高压压缩机，点燃燃气涡轮发动机， 以及在所述燃气涡轮发动机的操作速度下离合所述离合器。
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公开(公告)号：US20150361890A1
公开(公告)日：2015-12-17
申请号：US14740312
申请日：2015-06-16
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill
CPC classification number: F02C9/18 , F01D9/065 , F02C7/185 , Y02T50/671 , Y02T50/675
Abstract: A gas turbine engine includes a compressor section having a plurality of compressor stages, a combustor fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, the turbine section having at least one stage, a compressor bleed structure disposed in one of the plurality of compressor stages and operable to remove air from the compressor stage, a heat exchanger having an input connected to the compressor bleed, and an output connected to an active cooling system of at least one turbine stage, and wherein the compressor stage in which the compressor bleed structure is disposed includes airflow at a pressure above a minimum pressure threshold, and wherein the airflow has a temperature above a maximum temperature threshold.
Abstract translation: 燃气涡轮发动机包括具有多个压缩机级的压缩机部分，与压缩机部分流体连接的燃烧器，与燃烧器部分流体连接的涡轮机部分，具有至少一个级的涡轮机部分， 的多个压缩机级，并且可操作以从压缩机级移除空气，具有连接到压缩机排气口的输入端的热交换器和连接到至少一个涡轮级的主动冷却系统的输出，并且其中压缩机级 压缩机排气结构被布置成包括处于最高压力阈值以上的压力的气流，并且其中气流具有高于最大温度阈值的温度。
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公开(公告)号：US20150354465A1
公开(公告)日：2015-12-10
申请号：US14729002
申请日：2015-06-02
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill , Mark F. Zelesky
CPC classification number: F02C3/13 , F01D5/081 , F01D25/12 , F02C3/04 , F02C7/18 , F02C7/185 , F02C9/18 , F05D2260/213 , F05D2270/112 , F05D2270/20 , F05D2270/3032 , F05D2270/3062 , Y02T50/673 , Y02T50/676
Abstract: A turbine cooling air generation system for a gas turbine engine includes a first fluid pathway connecting a compressor bleed outlet and a mixing valve, a second fluid pathway connecting the compressor bleed outlet and an input of a heat exchanger, and a third fluid pathway connecting an output of the heat exchanger and the mixing valve. The mixing valve is further connected to an input of a turbine stage active cooling system.
Abstract translation: 一种用于燃气涡轮发动机的涡轮机冷却空气产生系统包括连接压缩机排气口和混合阀的第一流体路径，连接压缩机排气口和热交换器的输入口的第二流体路径，以及连接 输出热交换器和混合阀。 混合阀进一步连接到涡轮级主动冷却系统的输入端。
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Patent Agency Ranking
公开(公告)号：US20150354456A1
公开(公告)日：2015-12-10
申请号：US14732319
申请日：2015-06-05
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill
Abstract: A cooling system for gas turbine engines includes a turbine rotor compartment defining a cooling air plenum. A plurality of turbine discs are rotatably housed within the rotor compartment. A cooling air inlet is in fluid communication with the plenum. Each turbine disc includes a cooling outlet in fluid communication with the plenum for cooling the rotor compartment.
Abstract translation: 用于燃气涡轮发动机的冷却系统包括限定冷却空气室的涡轮转子隔室。 多个涡轮盘可旋转地容纳在转子室内。 冷却空气入口与气室流体连通。 每个涡轮盘包括一个冷却出口，该冷却出口与用于冷却转子室的增压室流体连通。
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公开(公告)号：US20150345392A1
公开(公告)日：2015-12-03
申请号：US14821409
申请日：2015-08-07
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Karl L. Hasel
CPC classification number: F02C7/06 , F01D25/162 , F02C3/04 , F02C3/107 , F02C7/36 , F02K3/00 , F02K3/04 , Y02T50/671 , Y10T29/4932
Abstract: A gas turbine engine includes a housing includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A rotor is connected to the hub and supports a compressor section. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. The radially inner boundary of the core inlet is at a location of a core inlet stator and the radially inner boundary of the compressor section inlet is at a location of the first stage low-pressure compressor rotor.
Abstract translation: 燃气涡轮发动机包括壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 转子连接到轮毂并支撑压缩机部分。 齿轮架构包括行星齿轮系。 风扇由齿轮架构旋转驱动。 第一和第二轴承分别相对于中间壳体和进气口支撑轴。 芯入口的径向内边界处于芯入口定子的位置，压缩机部分入口的径向内边界位于第一级低压压缩机转子的位置。
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公开(公告)号：US20150267617A1
公开(公告)日：2015-09-24
申请号：US14729800
申请日：2015-06-03
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Allan R. Penda , Brian D. Merry , Christopher M. Dye , Nathan Snape
CPC classification number: F02C7/185 , F02C7/08 , F02C7/14 , F02C7/18 , Y02T50/671
Abstract: A thermal system for a gas turbine engine includes a bypass flow duct and a compressor flow duct which meets with the bypass flow duct at an intersection. A valve is located within the intersection and is movable between a first position and a second position. First position is operable to selectively communicate fan bypass flow from the bypass flow duct and block the compressor flow duct. The second position is operable to selectively block the bypass flow duct and communicate bleed flow through the compressor flow duct.
Abstract translation: 用于燃气涡轮发动机的热系统包括在交叉口处与旁路流动管道相交的旁通流动管道和压缩机流动管道。 阀位于交叉口内，并可在第一位置和第二位置之间移动。 第一位置可操作以选择性地使来自旁路流动管道的风扇旁路流动并且阻塞压缩机流动管道。 第二位置可操作以选择性地阻挡旁路流动管道并且连通通过压缩机流动管道的排出流。
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公开(公告)号：US09121367B2
公开(公告)日：2015-09-01
申请号：US13869057
申请日：2013-04-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Hasel Karl , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
CPC classification number: F02K3/025 , F02C3/107 , F02C7/00 , F02K3/06 , F05D2260/4031
Abstract: A gas turbine engine has a fan section, a gear arrangement configured to drive the fan section, a compressor section, including both a low pressure compressor section and a high pressure compressor section. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section is greater than about 35. The pressure ratio across a first of the low and high pressure compressor sections is between about 3 and about 8. The pressure ratio across a second of the low and high pressure compressor sections is between about 7 and about 15. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.
Abstract translation: 燃气涡轮发动机具有风扇部，构造成驱动风扇部的齿轮装置，包括低压压缩部和高压压缩部两者的压缩部。 涡轮部分构造成驱动压缩机部分和齿轮装置。 通过低压压缩机部分的压力比和高压压缩机部分的压力比的组合提供的总压力比大于约35。第一低压压缩机部分和高压压缩机部分之间的压力比在 约3和约8之间。跨过第二个低压和高压压缩机段的压力比在约7至约15之间。风扇构造成将一部分空气输送到压缩机部分中，并且一部分空气进入 旁路管道。
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公开(公告)号：US20150113945A1
公开(公告)日：2015-04-30
申请号：US14512520
申请日：2014-10-13
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry
CPC classification number: F02K1/72 , F02K1/66 , F02K1/763 , F02K3/06 , F05B2250/314 , F05D2260/403
Abstract: A gas turbine engine that has a fan case radially surrounding a fan hub, and plural fan exit guide vanes rotatably connected between the fan hub and the fan case. The fan section also has a thrust reverser opening within the case, axially upstream of the guide vanes. The gas turbine engine also has a core case containing a core engine.
Abstract translation: 一种燃气涡轮发动机，其具有径向围绕风扇轮毂的风扇壳体，以及可旋转地连接在风扇轮毂和风扇壳体之间的多个风扇出口导向叶片。 风扇部分还具有在壳体内的导向叶片的轴向上游的推力反向器开口。 燃气涡轮发动机也具有包含核心发动机的铁心壳。
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