公开(公告)号：US20190024581A1

公开(公告)日：2019-01-24

申请号：US16143662

申请日：2018-09-27

Applicant: United Technologies Corporation

Inventor： Jonathan Gilson ,  Bruce L. Morin ,  Ramons A. Reba ,  David A. Topol ,  Wesley K. Lord

IPC: F02C3/107 ,  F01D25/16 ,  F02K3/06 ,  F04D29/54 ,  F04D29/66 ,  F01D9/04

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.

公开(公告)号：US09879611B2

公开(公告)日：2018-01-30

申请号：US14754298

申请日：2015-06-29

Applicant: United Technologies Corporation

Inventor： Bruce L. Morin ,  David A. Topol ,  Mark Boyer ,  Brian Desfosses ,  W. Marshall Quin ,  John Holchin ,  Jonathan D. Little ,  Bryan Roseberry

IPC: F04D27/02 ,  F02C6/08 ,  F02C9/18 ,  F01D17/10 ,  F04D29/66 ,  F16K47/04 ,  F16K3/02 ,  F02C3/13 ,  F04D29/52

CPC classification number: F02C9/18 ,  F01D17/105 ,  F02C3/13 ,  F02C6/08 ,  F04D27/0215 ,  F04D27/023 ,  F04D29/522 ,  F04D29/665 ,  F05D2260/36 ,  F05D2260/963 ,  F16K3/02 ,  F16K47/04

Abstract: Bleed valve assemblies in a gas turbine engine are disclosed herein. A bleed valve assembly in a low pressure compressor may include a bleed valve and a resonator chamber. A manifold may allow passage of air from a bleed duct into the resonator chamber. The resonator chamber may alter resonation properties of the bleed duct in order to prevent damage to components in the low pressure compressor.

公开(公告)号：US09733266B2

公开(公告)日：2017-08-15

申请号：US15270027

申请日：2016-09-20

Applicant: United Technologies Corporation ,  MTU Aero Engines AG

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

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

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, a turbine section having a first turbine including a first turbine rotor, a compressor rotor, and a gear reduction configured to effect a reduction in a speed of the fan relative to an input speed from the first turbine rotor. Each of the compressor rotor and the first turbine rotor includes a number of blades in each of a plurality of blade rows, the number of blades configured to operate at least some of the time at a rotational speed, 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 rotor, but does not hold true for any of the blade rows of the compressor rotor: (number of blades×rotational speed)/60≧5500, and the rotational speed being an approach speed in revolutions per minute.

公开(公告)号：US20170191415A1

公开(公告)日：2017-07-06

申请号：US15270027

申请日：2016-09-20

Applicant: United Technologies Corporation ,  MTU Aero Engines AG

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

IPC: F02C7/045 ,  F02K3/06 ,  F02C7/36 ,  F02C3/10

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, a turbine section having a first turbine including a first turbine rotor, a compressor rotor, and a gear reduction configured to effect a reduction in a speed of the fan relative to an input speed from the first turbine rotor. Each of the compressor rotor and the first turbine rotor includes a number of blades in each of a plurality of blade rows, the number of blades configured to operate at least some of the time at a rotational speed, 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 rotor, but does not hold true for any of the blade rows of the compressor rotor: (number of blades×rotational speed)/60≧5500, and the rotational speed being an approach speed in revolutions per minute.

公开(公告)号：US20160177774A1

公开(公告)日：2016-06-23

申请号：US14606087

申请日：2015-01-27

Applicant: United Technologies Corporation

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

IPC: F01D17/10 ,  F01D15/12 ,  F01D9/04 ,  F01D5/02 ,  F01D5/12

CPC classification number: F01D17/105 ,  F01D5/02 ,  F01D5/12 ,  F01D5/16 ,  F01D9/041 ,  F01D15/12 ,  F01D25/04 ,  F02C3/107 ,  F02C7/24 ,  F02C7/36 ,  F02K3/06 ,  F05D2200/36 ,  F05D2210/31 ,  F05D2220/32 ,  F05D2220/327 ,  F05D2240/301 ,  F05D2240/307 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/673

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.

Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机包括涡轮机部分，其包括风扇驱动涡轮机，由风扇驱动涡轮机驱动的齿轮架构，以及由风扇驱动涡轮经由齿轮传动驱动的风扇 建筑。 涡轮部分的至少一个级包括可旋转刀片阵列和一组叶片。 叶片数与叶片数之比大于或等于约1.55。 叶片的机械末端旋转马赫数被配置为在接近速度下大于或等于约0.5。

公开(公告)号：US20160090909A1

公开(公告)日：2016-03-31

申请号：US14964727

申请日：2015-12-10

Applicant: United Technologies Corporation

Inventor： Jonthan Gilson ,  Burce L. Morin ,  Ramons A. Reba ,  David A. Topol ,  Wesley K. Lord

IPC: F02C3/107 ,  F01D9/04

CPC classification number: F02C3/107 ,  F01D9/041 ,  F01D25/162 ,  F02K3/06 ,  F04D29/542 ,  F04D29/544 ,  F04D29/664 ,  F04D29/667 ,  F05D2220/36 ,  F05D2250/191 ,  F05D2250/38 ,  F05D2260/40311 ,  F05D2260/96 ,  F05D2260/961 ,  F05D2300/603

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.

Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的风扇部分包括具有风扇叶片的风扇转子和位于风扇转子下游的多个风扇出口导向叶片。 风扇转子被构造成通过齿轮减速被驱动。 定义了多个风扇出口导向叶片与多个风扇叶片的比例。 风扇出口导向叶片具有优化的扫掠和优化的倾斜。

公开(公告)号：US20160003264A1

公开(公告)日：2016-01-07

申请号：US14768839

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David A. Topol ,  Dilip Prasad

IPC: F04D29/66 ,  F01D5/14

CPC classification number: F04D29/666 ,  F01D5/06 ,  F01D5/10 ,  F01D5/145 ,  F04D29/321 ,  F05D2220/36 ,  F05D2260/961 ,  Y02T50/671 ,  Y02T50/673

Abstract: In accordance with one aspect of the disclosure, a rotor for a gas turbine engine is disclosed. The rotor may include a rotor disk and a plurality of blade extending radially outward from the rotor disk. At least one of the blades may have a physical nonuniformity. The blades may be distributed about the rotor disk based on any physical nonuniformities of the blades to generate at least one decay-resistant harmonic.

Abstract translation: 根据本公开的一个方面，公开了一种用于燃气涡轮发动机的转子。 转子可以包括转子盘和从转子盘径向向外延伸的多个叶片。 至少一个叶片可能具有物理不均匀性。 叶片可以基于叶片的任何物理不均匀性而围绕转子盘分布以产生至少一个抗衰减谐波。

公开(公告)号：US20140318147A1

公开(公告)日：2014-10-30

申请号：US14144710

申请日：2013-12-31

Applicant: United Technologies Corporation

Inventor： David A. Topol ,  Bruce L. Morin

IPC: F02C3/10 ,  F02C7/36

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， 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：US20140271112A1

公开(公告)日：2014-09-18

申请号：US13970670

申请日：2013-08-20

Applicant: United Technologies Corporation

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

IPC: F02C7/24

CPC classification number: F02C7/24 ,  F02K3/06 ,  F05D2200/36 ,  F05D2210/31 ,  F05D2240/301 ,  F05D2240/307 ,  Y02T50/673

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 compressor section driven by the turbine section, 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.

Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机包括涡轮部分，其包括风扇驱动涡轮机，由涡轮机部分驱动的压缩机部分，由风扇驱动涡轮机驱动的齿轮架构，以及风扇 由风扇驱动器通过齿轮架构驱动。 涡轮部分的至少一个级包括可旋转刀片阵列和一组叶片。 叶片数与叶片数之比大于或等于约1.55。 叶片的机械末端旋转马赫数被配置为在接近速度下大于或等于约0.5。

公开(公告)号：US20140219792A1

公开(公告)日：2014-08-07

申请号：US13721498

申请日：2012-12-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David A. Topol ,  Glen E. Potter ,  Flavien L. Thomas

IPC: F01D9/04 ,  F04D29/54

CPC classification number: F01D9/041 ,  F01D5/142 ,  F01D5/145 ,  F02C7/045 ,  F04D29/544 ,  F04D29/666 ,  F05D2250/31 ,  F05D2260/4031 ,  F05D2260/96 ,  F05D2260/961 ,  Y02T50/673 ,  Y10T29/49245

Abstract: A disclosed fan section of a gas turbine engine includes a fan rotor having a plurality of fan blades and a duct defining a passageway aft of the fan rotor. A fan exit guide vane is disposed within the duct downstream of the fan blades. The fan exit guide vane includes a plurality of exit guide vanes positioned downstream of the fan rotor with at least two of the plurality of exit guide vanes including different aft geometries for guiding airflow through the passage to reduce pressure distortions at the fan blades.

Abstract translation: 燃气涡轮发动机的公开的风扇部分包括具有多个风扇叶片的风扇转子和限定风扇转子后部的通道的管道。 风扇出口导叶设置在风扇叶片下游的管道内。 风扇出口导叶包括位于风扇转子下游的多个出口导向叶片，其中至少两个出口导向叶片包括不同的后部几何形状，用于引导气流通过通道以减小风扇叶片处的压力变形。