-
公开(公告)号：US20140165534A1
公开(公告)日：2014-06-19
申请号：US14179714
申请日：2014-02-13
Applicant: United Technologies Corporation
Inventor： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC: F02K3/06
CPC classification number: F02K3/06 , F02C3/107 , F05D2260/4031
Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor, with the overall pressure ratio being greater than or equal to about 35. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. A bypass ratio, which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section, is greater than or equal to about 8.
Abstract translation: 一种燃气涡轮发动机具有风扇部分，包括风扇，构造成驱动风扇部分的齿轮装置和包括第一压缩机和第二压缩机的压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 总压力比由第一压缩机和第二压缩机的组合提供，总压力比大于或等于约35.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 的空气进入旁路管道。 旁路比被定义为与通过压缩机部分的空气体积相比通过旁通管道的空气体积大于或等于约8。
-
公开(公告)号：US20140157757A1
公开(公告)日：2014-06-12
申请号：US14179799
申请日：2014-02-13
Applicant: United Technologies Corporation
Inventor： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC: F02K3/06
CPC classification number: F02K3/06 , F02C3/107 , F05D2260/4031
Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. The turbine section includes a fan drive turbine configured to drive the fan section, a pressure ratio across the fan drive turbine being greater than or equal to about 5. An overall pressure ratio is provided by the combination of the first compressor and the second compressor.
Abstract translation: 一种燃气涡轮发动机具有风扇部分，包括风扇，构造成驱动风扇部分的齿轮装置和包括第一压缩机和第二压缩机的压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 涡轮部分包括风扇驱动涡轮机，其构造成驱动风扇部分，风扇驱动涡轮机的压力比大于或等于约5.总压力比由第一压缩机和第二压缩机的组合提供。
-
公开(公告)号：US20130239587A1
公开(公告)日：2013-09-19
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
IPC: F02C7/00
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。
-
公开(公告)号：US10830148B2
公开(公告)日：2020-11-10
申请号：US15978455
申请日：2018-05-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry , Wesley K. Lord
Abstract: A gas turbine engine includes a main compressor. A tap is fluidly connected downstream of the main compressor. A heat exchanger is fluidly connected downstream of the tap. An auxiliary compressor unit is fluidly connected downstream of the heat exchanger. The auxiliary compressor unit is configured to compress air cooled by the heat exchanger with an overall auxiliary compressor unit pressure ratio between 1.1 and 6.0. An intercooling system for a gas turbine engine is also disclosed.
-
公开(公告)号：US10718268B2
公开(公告)日：2020-07-21
申请号：US15807911
申请日：2017-11-09
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry , Wesley K. Lord
Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses cooling air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.
-
Patent Agency Ranking
66.发明申请公开(公告)号：US20200049077A1
公开(公告)日：2020-02-13
申请号：US16598048
申请日：2019-10-10
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Daniel Bernard Kupratis , Brian D. Merry , Gabriel L. Suciu , William K. Ackermann
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 the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.
-
公开(公告)号：US10533501B2
公开(公告)日：2020-01-14
申请号：US15186722
申请日：2016-06-20
Applicant: United Technologies Corporation
Inventor： Stephen H. Taylor , Charles E. Lents , Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler
Abstract: A gas turbine engine includes a main compressor section. A booster compressor includes an inlet and an outlet. The inlet receives airflow from the main compressor section and the outlet provides airflow to a pneumatic system. A recirculation passage is between the inlet and the outlet. A flow splitter valve controls airflow between the outlet and the inlet through the recirculation passage for controlling airflow to the pneumatic system based on airflow output from the booster compressor. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.
-
公开(公告)号：US10519963B2
公开(公告)日：2019-12-31
申请号：US15186739
申请日：2016-06-20
Applicant: United Technologies Corporation
Inventor： Stephen H. Taylor , Charles E. Lents , Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler
IPC: F02C6/08 , F04D27/02 , F01D5/02 , F01D15/08 , F01D15/12 , F01D17/14 , F04D29/32 , F04D27/00 , F04D25/06 , F02C9/18
Abstract: A gas turbine engine includes a main engine compressor section. A booster compressor changes a pressure of airflow received from the main engine compressor section to a pressure desired for a pneumatic system. The booster compressor is configured to operate at airflow conditions greater than a demand of the pneumatic system. An exhaust valve controls airflow between an exhaust outlet and an outlet passage to the pneumatic system. The exhaust valve is operable to exhaust airflow from the booster compressor in excess of the demand of the pneumatic system. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.
-
公开(公告)号：US10352247B2
公开(公告)日：2019-07-16
申请号：US14767477
申请日：2014-02-27
Applicant: United Technologies Corporation
Inventor： William G. Sheridan , Gabriel L. Suciu , Brian D. Merry
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.
-
公开(公告)号：US10330010B2
公开(公告)日：2019-06-25
申请号：US14967518
申请日：2015-12-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler , William K. Ackermann , Matthew R. Feulner , Om P. Sharma
Abstract: A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.
-
-
-
-
-
-
-
-
-
Search Results
173
records
(took 0.023 seconds)
