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公开(公告)号：US09816436B2
公开(公告)日：2017-11-14
申请号：US14283610
申请日：2014-05-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jorn A. Glahn , William K. Ackermann , Clifton J. Crawley , Philip S. Stripinis
CPC classification number: F02C6/08 , F01D25/18 , F01D25/183 , F02C7/12 , F02C7/14 , F05D2260/601 , Y02T50/675
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft, a first bearing structure and a second bearing structure that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains the lubricant within the bearing compartments. A buffer system is configured to pressurize the seals to prevent the lubricant from escaping the bearing compartments. The buffer system includes a first circuit configured to supply a first buffer supply air to the first bearing structure, a second circuit configured to supply a second buffer supply air to the second bearing structure, and a controller configured to select between at least two bleed air supplies to communicate the first buffer supply air and the second buffer supply air.
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公开(公告)号：US20170233103A1
公开(公告)日：2017-08-17
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：US20140318143A1
公开(公告)日：2014-10-30
申请号：US14283610
申请日：2014-05-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jorn A. Glahn , William K. Ackermann , Clifton J. Crawley , Philip S. Stripinis
CPC classification number: F02C6/08 , F01D25/18 , F01D25/183 , F02C7/12 , F02C7/14 , F05D2260/601 , Y02T50/675
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft, a first bearing structure and a second bearing structure that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains the lubricant within the bearing compartments. A buffer system is configured to pressurize the seals to prevent the lubricant from escaping the bearing compartments. The buffer system includes a first circuit configured to supply a first buffer supply air to the first bearing structure, a second circuit configured to supply a second buffer supply air to the second bearing structure, and a controller configured to select between at least two bleed air supplies to communicate the first buffer supply air and the second buffer supply air.
Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机尤其包括支撑轴的轴，第一轴承结构和第二轴承结构。 第一轴承结构和第二轴承结构中的每一个包括轴承室，其包含润滑剂和在轴承隔室内容纳润滑剂的密封件。 缓冲系统被配置为对密封件加压以防止润滑剂从轴承隔间逸出。 缓冲系统包括被配置为向第一轴承结构提供第一缓冲器供应空气的第一电路，被配置为将第二缓冲器供应空气供应到第二轴承结构的第二电路以及被配置为在至少两个放气 用于通信第一缓冲器供应空气和第二缓冲器供应空气。
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公开(公告)号：US20140090355A1
公开(公告)日：2014-04-03
申请号：US13741425
申请日：2013-01-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Denman H. James , Jorn A. Glahn
IPC: F02C7/06
CPC classification number: F02C7/06 , F01D25/20 , F02K3/00 , F05D2220/36 , F05D2260/40311 , F16N2210/02 , Y02T50/671 , Y10T29/49236
Abstract: A disclosed lubrication system for a gas turbine engine includes a primary passage defining a flow path for lubricant to a gas turbine engine and a bypass passage defining a flow path for lubricant around the gas turbine engine. The lubrication system further includes a primary lubrication pump including a reduced total flow capacity of lubricant with a reduced bypass lubricant flow relative to the total overall flow capacity.
Abstract translation: 所公开的用于燃气涡轮发动机的润滑系统包括限定用于燃气涡轮发动机的润滑剂的流路的主通道和限定燃气涡轮发动机周围润滑剂的流路的旁路通道。 润滑系统还包括主润滑泵，其包括相对于总总流量减少的旁路润滑剂流量减少了润滑剂的总流量。
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公开(公告)号：US10787277B2
公开(公告)日：2020-09-29
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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Patent Agency Ranking
公开(公告)号：US10247095B2
公开(公告)日：2019-04-02
申请号：US13741425
申请日：2013-01-15
Applicant: United Technologies Corporation
Inventor： Denman H. James , Jorn A. Glahn
Abstract: A disclosed lubrication system for a gas turbine engine includes a primary passage defining a flow path for lubricant to a gas turbine engine and a bypass passage defining a flow path for lubricant around the gas turbine engine. The lubrication system further includes a primary lubrication pump including a reduced total flow capacity of lubricant with a reduced bypass lubricant flow relative to the total overall flow capacity.
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公开(公告)号：US10107131B2
公开(公告)日：2018-10-23
申请号：US14769959
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Jorn A. Glahn
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section, a shaft including a bearing system, a turbine section in communication with the shaft, a speed change mechanism coupling the fan section to the turbine section and a biasing device configured to apply a biasing force against the shaft.
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公开(公告)号：US10047677B2
公开(公告)日：2018-08-14
申请号：US14755036
申请日：2015-06-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jorn A. Glahn , Clifton J. Crawley, Jr. , Philip S. Stripinis , William K. Ackermann
IPC: F02C9/18 , F02C7/18 , F02C6/08 , F01D11/04 , F01D25/16 , F02C7/06 , F02C7/12 , F02C7/28 , F01D25/00
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. A buffer system includes a first circuit that supplies a first buffer supply air and a second circuit that supplies a second buffer supply air. The first circuit includes a first bleed air supply and a second bleed air supply. The second circuit includes a third bleed air supply and a fourth bleed air supply and at least one of the first circuit and the second circuit includes a variable area ejector.
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公开(公告)号：US20170130732A1
公开(公告)日：2017-05-11
申请号：US14934303
申请日：2015-11-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Jorn A. Glahn
CPC classification number: F04D29/083 , F01D11/001 , F01D11/02 , F04D29/324 , F04D29/522 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2220/3219
Abstract: A gas turbine engine compressor section has a hub carrying a last row of compressor blades. A compressor exit guide vane is downstream of the last row of compressor blades. A housing is radially inward of the compressor exit guide vane. A non-contact seal is positioned on one of the housing and the hub.
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公开(公告)号：US20160053631A1
公开(公告)日：2016-02-25
申请号：US14933440
申请日：2015-11-05
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Jorn A. Glahn
CPC classification number: F01D25/162 , F02C7/06 , F02C7/36 , F02K3/072 , F05D2240/50 , F05D2260/40311
Abstract: A turbine section of a gas turbine engine according to an example of the present disclosure includes, among other things, a first turbine section and a second turbine section. The first turbine section has a first exit area and rotates at a first speed. The second turbine section has a second exit area and rotates at a second speed. A first performance quantity is defined as the product of the first speed squared and the first exit area. A second performance quantity is defined as the product of the second speed squared and the second exit area.
Abstract translation: 根据本公开的示例的燃气涡轮发动机的涡轮部分包括第一涡轮部分和第二涡轮部分。 第一涡轮部分具有第一出口区域并以第一速度旋转。 第二涡轮部分具有第二出口区域并以第二速度旋转。 第一性能数量被定义为第一速度平方和第一出口区域的乘积。 第二性能量被定义为第二速度平方和第二出口区的乘积。
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