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11.发明申请ENGINE MID-TURBINE FRAME TRANSFER TUBE FOR LOW PRESSURE TURBINE CASE COOLING 审中-公开发动机用于低压涡轮机箱冷却的中涡轮机架转子管公开(公告)号：US20160032775A1
公开(公告)日：2016-02-04
申请号：US14773876
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Cheng-Zhang Wang , Jorn A. Glahn , David F. Cloud , Peter M. Munsell , Clifton J. Crawley, JR. , Robert Newman , Michelle Diana Stearns
IPC: F01D25/24
CPC classification number: F01D25/24 , F01D9/041 , F01D9/065 , F01D25/162 , F02C7/18 , F05D2240/14 , F05D2260/14 , F05D2260/20 , F05D2260/2212 , F05D2260/97 , Y02T50/676
Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.
Abstract translation: 涡轮发动机包括具有低压涡轮机的涡轮机部分和围绕轴线布置的涡轮机壳体。 框架组件限定外腔和内腔，其中外腔包括构造并适于将冷却空气与涡轮机壳连通的至少一个开口。 传送管设置在外腔内并且被配置和适于接收冷却空气。 传送管包括弯曲部，该弯曲部被配置为向外腔内的冷却空气赋予圆周速度。
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公开(公告)号：US10823075B2
公开(公告)日：2020-11-03
申请号：US15160365
申请日：2016-05-20
Applicant: United Technologies Corporation
Inventor： Jorn A. Glahn , Denman H. James , Amy R. Grace
IPC: F02C7/24 , F01D21/14 , F02C7/224 , F01D21/12 , F02C7/14 , F01D25/18 , F02C9/28 , F02C3/04 , F02C7/06 , F02C7/32
Abstract: According to an aspect, a method includes predicting, by a processor, a projected oil-wetted metal temperature in a lubrication system of a gas turbine engine at shutdown based on one or more thermal models prior to shutdown of the gas turbine engine. The processor determines a coking index based on the projected oil-wetted metal temperature and a coking limit threshold associated with one or more engine components. An oil coking mitigation action is triggered as a shutdown management event of the gas turbine engine based on the coking index.
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公开(公告)号：US20180327117A1
公开(公告)日：2018-11-15
申请号：US16034550
申请日：2018-07-13
Applicant: United Technologies Corporation
Inventor： Matthew D. Teicholz , Jeffrey W. Sutliff , William H. Greene, JR. , Kenneth J. White , Matthew R. Feulner , John P. Virtue, JR. , Jorn A. Glahn , Philip D. Hoover , Victor M. Pinedo , Jason B. Solomonides
Abstract: A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed, where the controller modulates a duty cycle of the discrete starter valve via pulse width modulation.
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公开(公告)号：US20180265223A1
公开(公告)日：2018-09-20
申请号：US15985782
申请日：2018-05-22
Applicant: United Technologies Corporation
Inventor： Matthew D. Teicholz , Jeffrey W. Sutliff , William H. Greene, JR. , Kenneth J. White , Matthew R. Feulner , John P. Virtue, JR. , Jorn A. Glahn , Philip D. Hoover , Victor M. Pinedo , Jason B. Solomonides
CPC classification number: B64F1/34 , B64D27/16 , F02C7/27 , F02C7/277 , F05D2220/323 , F05D2260/85 , F05D2270/303 , F05D2270/71
Abstract: A system for controlling a start sequence of a gas turbine engine includes an electronic engine control system, a thermal model, memory, a model for determining a time period (fmotoring), and a controller. The thermal model synthesizes a heat state of the gas turbine engine. The memory records the current heat state at shutdown and a shutdown time of the gas turbine engine. The model for determining the time period is for motoring the gas turbine engine at a predetermined speed Ntarget that is less than a speed to start the gas turbine engine, where tmotoring is a function of the heat state recorded at engine shutdown and an elapsed time of an engine start request relative to a previous shutdown time. The controller modulates a starter valve to maintain the gas turbine engine within a predetermined speed range of NtargetMin to NtargetMax for homogenizing engine temperatures.
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公开(公告)号：US20170107839A1
公开(公告)日：2017-04-20
申请号：US14887013
申请日：2015-10-19
Applicant: United Technologies Corporation
Inventor： Jorn A. Glahn , Frederick M. Schwarz
CPC classification number: F01D11/025 , F01D5/02 , F01D5/082 , F01D11/001 , F01D11/02 , F01D11/04 , F02C3/04 , F04D29/083 , F04D29/321 , F05D2220/323 , F05D2240/35 , F05D2240/50 , F05D2260/14 , F05D2260/15 , Y02T50/676
Abstract: Aspects of the disclosure are directed to an engine of an aircraft comprising: a first seal located forward of a disk of a turbine section of the engine, a second seal located forward of the disk of the turbine section and radially inward of the first seal relative to an axial centerline of the engine, where the first and second seals are floating, non-contact seals.
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Patent Agency Ranking
16.发明申请GAS TURBINE ENGINE WITH GEARED TURBOFAN AND OIL THERMAL MANAGEMENT SYSTEM WITH UNIQUE HEAT EXCHANGER STRUCTURE 审中-公开具有特殊热交换器结构的带齿轮涡轮机和油热管理系统的气体涡轮发动机公开(公告)号：US20150361887A1
公开(公告)日：2015-12-17
申请号：US14761427
申请日：2014-03-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ethan K. Stearns , Jorn A. Glahn , Daniel J. McKaveney
IPC: F02C7/06
CPC classification number: F02C7/06 , F02C3/32 , F02C7/14 , F02C7/224 , F02C7/36 , F02C9/18 , F05D2260/213 , F05D2260/601 , Y02T50/676
Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.
Abstract translation: 用于燃气涡轮发动机的供油系统具有向出口管线输送润滑剂的润滑剂泵。 出口管线被分成至少一个热管线并进入冷却管线，热管线主要指向与不用于接收较冷润滑剂的发动机相关联的位置，并且冷管线通过一个或多个热交换器引导 哪种润滑剂被冷却。 然后，冷线路路由到相关联的燃气涡轮发动机的风扇驱动齿轮系统。 公开了一种方法和装置。 热交换器至少包括空气/油冷却器，其中空气被拉过空气/油冷却器以冷却油。 空气/油冷却器设置有从压缩机部分抽出压缩空气的喷射器，以增加空气/油冷却器的气流。
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公开(公告)号：US09027353B2
公开(公告)日：2015-05-12
申请号：US14219070
申请日：2014-03-19
Applicant: United Technologies Corporation
Inventor： Jorn A. Glahn , Clifton J. Crawley, Jr. , Philip S. Stripinis , William K. Ackermann
IPC: F02C6/08 , F01D25/00 , F02C7/18 , F01D11/04 , F01D25/16 , F02C7/06 , F02C7/12 , F02C7/28 , F02C9/18
CPC classification number: F02C9/18 , F01D11/04 , F01D25/00 , F01D25/16 , F02C6/08 , F02C7/06 , F02C7/12 , F02C7/18 , F02C7/28 , F05D2260/601 , Y02T50/675 , Y10T29/49229
Abstract: A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicates buffer air to a portion of the gas turbine engine. The buffer system includes a first circuit configured to selectively mix a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure.
Abstract translation: 燃气涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器，与燃烧器流体连通的涡轮机部分，经由齿轮架构被涡轮部分驱动的风扇部分和缓冲系统， 将缓冲空气传送到燃气涡轮发动机的一部分。 缓冲系统包括第一回路，其被配置为选择性地混合具有第一压力的第一排放空气供应源和第二排气源，其具有大于第一压力的第二压力，以提供具有中间压力的第一缓冲器供应空气， 第一压力和第二压力。
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公开(公告)号：US10040577B2
公开(公告)日：2018-08-07
申请号：US15042363
申请日：2016-02-12
Applicant: United Technologies Corporation
Inventor： Matthew D. Teicholz , Jeffrey W. Sutliff , William H. Greene, Jr. , Kenneth J. White , Matthew R. Feulner , John P. Virtue, Jr. , Jorn A. Glahn , Philip D. Hoover , Victor M. Pinedo , Jason B. Solomonides
CPC classification number: B64F1/34 , B64D27/16 , F02C7/27 , F02C7/277 , F05D2220/323 , F05D2260/85 , F05D2270/303 , F05D2270/71
Abstract: A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed.
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公开(公告)号：US20160024968A1
公开(公告)日：2016-01-28
申请号：US14774412
申请日：2014-03-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ethan K. Stearns , Jorn A. Glahn , Daniel J. McKaveney
CPC classification number: F01D25/20 , F01D25/12 , F01D25/125 , F01D25/18 , F01M1/12 , F02C7/06 , F02C7/14 , F02C7/185 , F02C7/224 , F02C9/18 , F05D2220/32 , F05D2220/323 , F05D2240/35 , F05D2260/205 , F05D2260/213 , F05D2260/232 , F05D2260/40311 , F05D2260/601 , F05D2260/606 , F05D2260/98 , Y02T50/671 , Y02T50/675
Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.
Abstract translation: 用于燃气涡轮发动机的供油系统具有向出口管线输送润滑剂的润滑剂泵。 出口管线被分成至少一个热管线并进入冷却管线，热管线主要指向与不用于接收较冷润滑剂的发动机相关联的位置，并且冷管线通过一个或多个热交换器 哪种润滑剂被冷却。 然后，冷线路路由到相关联的燃气涡轮发动机的风扇驱动齿轮系统。 公开了一种方法和装置。 热交换器至少包括空气/油冷却器，其中空气被拉过空气/油冷却器以冷却油。 空气/油冷却器设置有从压缩机部分抽出压缩空气的喷射器，以增加空气/油冷却器的气流。
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公开(公告)号：US20140130479A1
公开(公告)日：2014-05-15
申请号：US13719620
申请日：2012-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Jorn A. Glahn
IPC: F02K3/075
Abstract: A gas turbine engine includes a very high speed low-pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for a higher pressure turbine is at a ratio between about 0.5 and about 1.5. In addition, the lower pressure turbine is mounted with a first bearing mounted in a mid-turbine frame, and a second bearing mounted within a turbine exhaust case.
Abstract translation: 燃气涡轮发动机包括非常高速的低压涡轮机，使得由与较高压力涡轮机的相同参数相比较，由低压涡轮机的出口面积乘以低压涡轮机转速的平方而定义的量在 约0.5至约1.5的比率。 此外，低压涡轮机安装有安装在中涡轮机架中的第一轴承和安装在涡轮机排气箱内的第二轴承。
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