公开(公告)号：US20180299477A1

公开(公告)日：2018-10-18

申请号：US16018754

申请日：2018-06-26

Applicant: United Technologies Corporation ,  MTU Aero Engines AG

Inventor： David A. Topol ,  Bruce L. Morin ,  Detlef Korte

IPC: G01P3/48 ,  F02C7/32 ,  F02K3/06 ,  F02C7/24 ,  F01D5/12 ,  F02C3/04 ,  F02C7/36 ,  F01D5/02 ,  F02C3/10

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: 5500≤(number of blades×rotational speed)/60≤10000, the rotational speed being in revolutions per minute.

公开(公告)号：US20180298828A1

公开(公告)日：2018-10-18

申请号：US16018640

申请日：2018-06-26

Applicant: United Technologies Corporation ,  MTU Aero Engines AG

Inventor： David A. Topol ,  Bruce L. Morin ,  Detlef Korte

IPC: F02C7/36 ,  F01D5/12 ,  F01D5/02

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)/60 s≥5500 Hz, and the rotational speed is in revolutions per minute.

公开(公告)号：US09957840B2

公开(公告)日：2018-05-01

申请号：US14760719

申请日：2014-02-19

Applicant: United Technologies Corporation

Inventor： David A. Topol ,  Bruce L. Morin ,  Dilip Prasad ,  Thomas J. Ouellette

IPC: F01D25/24 ,  F01D5/02 ,  F01D1/02 ,  F02C7/045

CPC classification number: F01D25/24 ,  F01D1/02 ,  F01D5/021 ,  F02C7/045 ,  F05D2220/32 ,  F05D2250/283 ,  F05D2260/96

Abstract: A gas turbine engine has a propulsor including a fan and a liner positioned upstream of the fan. The liner has a backing plate, a cellular structure with cells extending from the backing plate, and a perforated sheet with a depth defined as a distance between the perforated sheet and the backing sheet. The depth is selected to achieve a desired ratio of the depth relative to a gap?. A depth to gap ratio is substantially in a range of 0.035 to 0.08. A method is also disclosed.

公开(公告)号：US09726019B2

公开(公告)日：2017-08-08

申请号：US15259232

申请日：2016-09-08

Applicant: United Technologies Corporation

Inventor： David A. Topol ,  Bruce L. Morin

IPC: F02C3/10 ,  F02C7/24 ,  F02C7/32 ,  F02K3/06 ,  F01D5/02 ,  F01D5/12 ,  F02C7/36

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, a turbine section that has 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 one of a plurality of blade rows of the compressor rotor, and the blades are configured to operate at least some of the time at a rotational speed. The number of compressor blades in at least one of the blade rows and the rotational speed are such that the following formula holds true for the at least one of the plurality of blade rows of the compressor rotor: (the number of blades×the rotational speed)/60 sec≧about 5500 Hz. A method of designing a gas turbine engine is also disclosed.

公开(公告)号：US09650965B2

公开(公告)日：2017-05-16

申请号：US15014363

申请日：2016-02-03

Applicant: United Technologies Corporation

Inventor： David A. Topol ,  Bruce L. Morin ,  Detlef Korte

IPC: F02C7/24 ,  F02C3/10 ,  F02C7/32 ,  F02K3/06 ,  F02C7/36

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, a turbine section having a fan drive turbine rotor, and a compressor rotor. A gear reduction is configured to effect a reduction in a speed of the fan relative to an input speed from the fan drive turbine rotor. Each of the compressor rotor and the fan drive turbine rotor includes a number of blades in each of a plurality of blade rows. The number of blades are configured to operate at least some of the time at a rotational speed.

公开(公告)号：US20170122217A1

公开(公告)日：2017-05-04

申请号：US15404330

申请日：2017-01-12

Applicant: United Technologies Corporation ,  MTU Aero Engines AG

Inventor： David A. Topol ,  Bruce L. Morin ,  Detlef Korte

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/04

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 has a fan including a plurality of fan blades, a turbine section having a first turbine, a compressor, and a gear reduction positioned between the fan and the first turbine. Each of the compressor and the first turbine includes a number of blades in each of a plurality of blade rows, the number of blades rotatable at least some of the time at a rotational speed in operation, and the number of blades and the rotational speed being such that the following formula holds true for at least a majority of the blade rows of the first turbine, but does not hold true for any of the blade rows of the compressor: (number of blades×rotational speed)/60≧5500, and the rotational speed being an approach speed in revolutions per minute.

公开(公告)号：US20160298651A1

公开(公告)日：2016-10-13

申请号：US14680409

申请日：2015-04-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David A. Topol

IPC: F04D29/66 ,  F01D5/12 ,  F04D29/54 ,  F01D25/04 ,  F04D29/32 ,  F01D5/02 ,  F01D9/04

CPC classification number: F04D29/661 ,  F01D5/02 ,  F01D5/12 ,  F01D5/26 ,  F01D9/041 ,  F01D25/04 ,  F04D29/324 ,  F04D29/544 ,  F04D29/663 ,  F04D29/666 ,  F05D2260/96 ,  Y02T50/673

Abstract: An exemplary section of a gas turbine engine according to this disclosure includes, among other things, a first array of airfoils including a first number of airfoils, and a second array of airfoils downstream of the first array of airfoils. The second array includes a second number of airfoils. The second number of airfoils is at least 1.19 times the first number of airfoils thereby providing a predetermined modal.

Abstract translation: 根据本公开的燃气涡轮发动机的示例性部分尤其包括第一阵列的翼型件，其包括第一数量的翼型件，以及在第一翼型阵列下游的第二翼型阵列。 第二阵列包括第二数量的翼型。 第二数量的翼型件是第一数量的翼型件的至少1.19倍，从而提供预定的模态。

公开(公告)号：US20150337684A1

公开(公告)日：2015-11-26

申请号：US14760719

申请日：2014-02-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David A. Topol ,  Bruce L. Morin ,  Dilip Prasad ,  Thomas J. Ouellette

IPC: F01D25/24 ,  F01D1/02 ,  F01D5/02

CPC classification number: F01D25/24 ,  F01D1/02 ,  F01D5/021 ,  F02C7/045 ,  F05D2220/32 ,  F05D2250/283 ,  F05D2260/96

Abstract: A gas turbine engine has a propulsor including a fan and a liner positioned upstream of the fan. The liner has a backing plate, a cellular structure with cells extending from the backing plate, and a perforated sheet with a depth defined as a distance between the perforated sheet and the backing sheet. The depth is selected to achieve a desired ratio of the depth relative to a gap?. A depth to gap ratio is substantially in a range of 0.035 to 0.08. A method is also disclosed.

Abstract translation: 燃气涡轮发动机具有包括风扇和位于风扇上游的衬垫的推进器。 衬垫具有背板，具有从背板延伸的单元的多孔结构以及被定义为多孔板和背衬板之间距离的深度的多孔板。 选择深度以实现相对于间隙α的深度的期望比率。 深度与间隙比基本上在0.035至0.08的范围内。 还公开了一种方法。

公开(公告)号：US20150152787A1

公开(公告)日：2015-06-04

申请号：US14591975

申请日：2015-01-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David A. Topol ,  Bruce L. Morin

IPC: F02C7/24 ,  F02C7/36

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.

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， 转速为每分钟转。 还公开了一种设计燃气涡轮发动机和压缩机组件的方法。

公开(公告)号：US08834099B1

公开(公告)日：2014-09-16

申请号：US14159760

申请日：2014-01-21

Applicant: United Technologies Corporation

Inventor： David A. Topol ,  Bruce L. Morin

IPC: F01D1/02

CPC classification number: F01D5/12 ,  F01D5/02 ,  F05D2220/327 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/673

Abstract: A gas turbine engine comprises a fan and a turbine section having a first turbine rotor. The first turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from a fan drive turbine 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: (the number of blades×the rotational speed)/(60 seconds/minute)≧5500 Hz; and the rotational speed being in revolutions per minute. A compressor module and a method of designing a gas turbine engine are also disclosed.

Abstract translation: 燃气涡轮发动机包括风扇和具有第一涡轮转子的涡轮部分。 第一涡轮转子驱动压缩机转子。 齿轮减速效应相对于来自风扇驱动涡轮转子的输入速度降低了风扇的速度。 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的以下公式成立：（叶片数×转速）/（60秒/分钟）≥ 5500 Hz; 转速为每分钟转。 还公开了压缩机模块和设计燃气涡轮发动机的方法。