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公开(公告)号：US20200173370A1
公开(公告)日：2020-06-04
申请号：US16667326
申请日：2019-10-29
Applicant: United Technologies Corporation , MTU Aero Engines AG
Inventor： David A. Topol , Bruce L. Morin , Detlef Korte
Abstract: A gas turbine engine has a fan section including a fan, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, and a gear reduction. The low pressure compressor and the low pressure turbine have a number of blades in each of at least one of a plurality of blade rows. The blades are rotatable at least some of the time at a rotational speed in operation. The number of blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor turbine: (number of blades×rotational speed)/60s≥5500 Hz, and the rotational speed is in revolutions per minute.
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公开(公告)号：US10526914B2
公开(公告)日：2020-01-07
申请号：US14761689
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Bruce L. Morin , Wesley K. Lord
Abstract: In accordance with one aspect of the disclosure, a gas turbine engine, method of using and designing such is disclosed. The gas turbine engine may comprise a fan including a plurality of blades, and a variable area fan nozzle. The fan may be configured to have a design point fan tip leading edge relative flow angle βADP, and may be further configured to have an off-design point fan tip leading edge relative flow angle β at an off-design fan operating point. The variable area fan nozzle may be configured to manipulate the amount of air flowing through the fan so that the absolute value of a difference between the design point fan tip leading edge relative flow angle βADP and the off-design point fan tip leading edge relative flow angle β is in a specified range.
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公开(公告)号：US20180258857A1
公开(公告)日：2018-09-13
申请号：US15452634
申请日：2017-03-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dilip Prasad , Bruce L. Morin
CPC classification number: F02C7/045 , B64D2033/0206 , F01D25/06 , F02K1/827 , F02K3/06 , F05D2260/96 , F05D2260/963 , G10K11/172 , Y02T50/672
Abstract: Disclosed is a flutter damper including a first plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a first fan flutter mode, the first plurality of chambers in fluid communication with a flow surface, and a second plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a second fan flutter mode, the second plurality of chambers in fluid communication with the flow surface, and wherein the first plurality of chambers and second plurality of chambers are disposed in a grid pattern.
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公开(公告)号：US20180258853A1
公开(公告)日：2018-09-13
申请号：US15452604
申请日：2017-03-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ian T. Marchaj , Bruce L. Morin , Mani Sadeghi , Daniel L. Gysling
CPC classification number: F02C7/045 , B64D2033/0206 , F01D25/04 , F01D25/24 , F02K1/827 , F02K3/06 , F05D2220/323 , F05D2260/96 , F05D2260/963 , G10K11/172 , Y02T50/672
Abstract: Disclosed is a flutter damper, including an acoustic liner having a perforated radial inner face sheet and a radial outer back sheet, the acoustic liner being configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber secured to the radial outer back sheet, the chamber being in fluid communication with the acoustic liner, and the chamber being configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and at least one stiffening structure connected to a top surface of the chamber that tunes the top surface out of the frequency range associated with one or more fan flutter modes.
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公开(公告)号：US09624834B2
公开(公告)日：2017-04-18
申请号：US14591975
申请日：2015-01-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David A. Topol , Bruce L. Morin
CPC classification number: F02C7/36 , F01D5/02 , F01D5/12 , F05D2220/36 , F05D2260/40311 , F05D2260/96 , Y02T50/673 , Y10T29/49236 , Y10T29/4932
Abstract: A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor turbine: (number of blades×rotational speed)/60 s≧5500 Hz, and the rotational speed is in revolutions per minute. A method of designing a gas turbine engine and a compressor module are also disclosed.
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Patent Agency Ranking
公开(公告)号：US20160138474A1
公开(公告)日：2016-05-19
申请号：US14967478
申请日：2015-12-14
Applicant: United Technologies Corporation
Inventor： David A. Topol , Bruce L. Morin
CPC classification number: G01P3/48 , F01D5/02 , F01D5/12 , F02C3/04 , F02C3/10 , F02C7/24 , F02C7/32 , F02C7/36 , F02K3/06 , F05D2200/13 , F05D2200/14 , F05D2220/32 , F05D2220/36 , F05D2260/40311 , F05D2260/96 , Y02T50/673 , Y10T29/49236 , Y10T29/4932
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan and a turbine section having a fan drive turbine rotor, and a compressor rotor. A gear reduction effects a reduction in a speed of the fan relative to an input speed from the fan drive turbine rotor. The compressor rotor has a number of compressor blades in at least half of a plurality of blade rows of the compressor rotor. The blades are configured to operate at least some of the time at a rotational speed. The number of compressor blades in the at least half of the blade rows and the rotational speed is such that the following formula holds true for each row of the at least half of the blade rows of the compressor rotor: (the number of blades×the rotational speed)/60 s≧about 5500 Hz.
Abstract translation: 根据本公开的示例的燃气涡轮发动机尤其包括具有风扇驱动涡轮机转子和压缩机转子的风扇和涡轮部分。 相对于来自风扇驱动涡轮转子的输入速度，齿轮减速实现风扇速度的降低。 压缩机转子在压缩机转子的多个叶片列的至少一半中具有多个压缩机叶片。 叶片被构造成在转速下至少一些时间运行。 叶片行的至少一半中的压缩机叶片的数量和转速使得对于压缩机转子的至少一半叶片行的每一行，以下公式成立：（叶片数× 转速）/ 60s≧约5500Hz。
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公开(公告)号：US20160025004A1
公开(公告)日：2016-01-28
申请号：US14795911
申请日：2015-07-10
Applicant: United Technologies Corporation , MTU Aero Engines AG
Inventor： Bruce L. Morin , Detlef Korte
CPC classification number: F02C3/107 , F02K3/04 , F05D2220/32 , F05D2260/40311 , F05D2260/96
Abstract: A gas turbine engine comprises a fan, a compressor section including a compressor having a low pressure portion and a high pressure portion, a combustor section, and a turbine having a downstream portion. A gear reduction effects a reduction in the speed of the fan relative to an input speed to the fan. The downstream portion of the turbine has a number of turbine blades in each of a plurality of rows of the downstream turbine portion. The turbine blades operate at least some of the time at a rotational speed. The number of blades and the rotational speed are such that the following formula holds true for at least one of the blade rows of the downstream turbine: (number of blades×speed)/60≧5500. The rotational speed is an approach speed in revolutions per minute. A method of designing a gas turbine engine and a turbine module are also disclosed.
Abstract translation: 燃气涡轮发动机包括风扇，包括具有低压部分和高压部分的压缩机的压缩机部分，燃烧器部分和具有下游部分的涡轮机。 齿轮减速可以降低风扇相对于风扇输入速度的速度。 涡轮机的下游部分在下游涡轮部分的多排中的每一排中具有多个涡轮机叶片。 涡轮叶片在转速下至少部分时间运转。 叶片的数量和转速使得对于下游涡轮机的至少一个叶片排，以下公式成立：（叶片数×速度）/60≥5500。 旋转速度是每分钟转数的接近速度。 还公开了一种设计燃气涡轮发动机和涡轮模块的方法。
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公开(公告)号：US20150204238A1
公开(公告)日：2015-07-23
申请号：US14248386
申请日：2014-04-09
Applicant: UNITED TECHNOLOGIES CORPORATION , MTU AERO ENGINES AG
Inventor： Bruce L. Morin , Detlef Korte
CPC classification number: F02C3/113 , F02K3/04 , F05D2220/32 , F05D2260/40311 , F05D2260/96 , F16H1/28 , G06F17/5086 , Y02T50/671
Abstract: A gas turbine engine includes a fan, a turbine having a fan drive rotor, and a speed reduction device effecting a reduction in the speed of the fan relative to an input speed from the fan drive rotor. The fan drive rotor has a number of turbine blades in at least one of a plurality of rows of the fan drive rotor, and the turbine blades operating at least some of the time at a rotational speed, and the number of turbine blades in the at least one row and the rotational speed being such that the following formula holds true for the at least one row of the fan drive turbine (the number of blades×the rotational speed)/(60 seconds/minute)>4000 Hz. The rotational speed being in revolutions per minute. A method is also disclosed.
Abstract translation: 燃气涡轮发动机包括风扇，具有风扇驱动转子的涡轮机和相对于来自风扇驱动转子的输入速度降低风扇速度的减速装置。 风扇驱动转子在风扇驱动转子的多行中的至少一行中具有多个涡轮叶片，并且涡轮叶片以至少一些时间在转速下运行，并且涡轮叶片的数量在 至少一排，并且转速使得对于风扇驱动涡轮机的至少一排（叶片数×转速）/（60秒/分钟）> 4000Hz，以下公式成立。 转速为每分钟转。 还公开了一种方法。
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公开(公告)号：US20140003915A1
公开(公告)日：2014-01-02
申请号：US14016436
申请日：2013-09-03
Applicant: United Technologies Corporation
Inventor： David A. Topol , Bruce L. Morin
IPC: F02C7/24
CPC classification number: F02C3/10 , F01D5/02 , F01D5/12 , F02C7/24 , F02C7/36 , F05D2260/96 , Y02T50/673 , Y10T29/49236 , Y10T29/4932
Abstract: A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor turbine: (number of blades×rotational speed)/60 s≧5500 Hz, and the rotational speed is in revolutions per minute. A method of designing a gas turbine engine and a compressor module are also disclosed.
Abstract translation: 燃气涡轮发动机具有风扇和具有风扇驱动涡轮机转子的涡轮机。 风扇驱动涡轮转子驱动压缩机转子。 齿轮减速实现了风扇相对于来自驱动压缩机转子的风扇驱动涡轮转子的输入速度的降低。 压缩机转子在压缩机转子的多排中的至少一排中具有多个压缩机叶片。 叶片在旋转速度下至少运行一些时间。 至少一行中的压缩机叶片的数量和转速使得至少一排压缩机转子涡轮机的以下公式成立：（叶片数×转速）/ 60s> = 5500Hz，以及 旋转速度为每分钟转数。 还公开了一种设计燃气涡轮发动机和压缩机组件的方法。
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公开(公告)号：US11143109B2
公开(公告)日：2021-10-12
申请号：US16740611
申请日：2020-01-13
Applicant: United Technologies Corporation
Inventor： Bruce L. Morin , David A. Topol , Detlef Korte
IPC: F01D5/02 , F02C7/24 , F02K3/06 , F01D5/12 , F01D9/04 , F01D15/12 , F01D17/10 , F01D5/16 , F01D25/04 , F02C3/107 , F02C7/36
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.
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