公开(公告)号：US10443543B2

公开(公告)日：2019-10-15

申请号：US15343470

申请日：2016-11-04

Applicant: United Technologies Corporation

Inventor： John P. Virtue, Jr. ,  Rishon Saftler ,  Frederick M. Schwarz

IPC: F01D19/02 ,  F02K3/068 ,  F02K3/075 ,  F04D29/64 ,  F01D11/18 ,  F02K3/02 ,  F02K3/06 ,  F01D19/00 ,  F01D25/16 ,  F01D25/36 ,  F02C7/26 ,  F02C7/32 ,  F02C9/42 ,  F02K3/11 ,  B64D27/00

Abstract: An aspect includes a system including a high compressor of a gas turbine engine having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%. The cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine. The system also includes at least two bowed rotor management systems for the gas turbine engine to prevent damage to the rotor blades for a bowed rotor condition of the high compressor under a plurality of operating conditions.

公开(公告)号：US20180230946A1

公开(公告)日：2018-08-16

申请号：US15343470

申请日：2016-11-04

Applicant: United Technologies Corporation

Inventor： John P. Virtue, JR. ,  Rishon Saftler ,  Frederick M. Schwarz

IPC: F02K3/068 ,  F04D29/64 ,  F01D11/18 ,  F02K3/02 ,  F02K3/06 ,  F02K3/075 ,  B64D27/00 ,  F02K3/11 ,  F01D25/16

CPC classification number: F02K3/068 ,  B64D2027/005 ,  F01D11/18 ,  F01D19/00 ,  F01D25/16 ,  F01D25/164 ,  F01D25/36 ,  F02C7/26 ,  F02C7/32 ,  F02C9/42 ,  F02K3/025 ,  F02K3/06 ,  F02K3/075 ,  F02K3/11 ,  F04D29/642 ,  F05D2220/3219 ,  F05D2220/36 ,  F05D2260/80 ,  F05D2260/84 ,  F05D2260/85 ,  Y02T50/671

Abstract: An aspect includes a system including a high compressor of a gas turbine engine having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%. The cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine. The system also includes at least two bowed rotor management systems for the gas turbine engine to prevent damage to the rotor blades for a bowed rotor condition of the high compressor under a plurality of operating conditions.

公开(公告)号：US10018118B2

公开(公告)日：2018-07-10

申请号：US14762092

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Philip Robert Rioux ,  Rishon Saftler

IPC: F02C7/18 ,  F01D25/24 ,  F02C6/08

CPC classification number: F02C7/18 ,  F01D25/243 ,  F01D25/246 ,  F02C6/08 ,  F05D2240/12 ,  Y10T29/49828

Abstract: A splitter for protecting parts of a gas turbine engine is provided. The splitter segregates the flow of hot and cold gases into the air bleed manifold around the high compressor section to reduce maximum temperatures and minimize the temperature gradients of engine parts, especially inner case flanges The splitter divides the air bleed manifold into an annular inner cavity and an outer cavity. The splitter directs relatively cold air from the high compressor bleed ducts into the inner cavity and relatively hot air from the aft hub into the outer cavity, away from the inner case flanges.

公开(公告)号：US09677472B2

公开(公告)日：2017-06-13

申请号：US13646822

申请日：2012-10-08

Applicant: United Technologies Corporation

Inventor： Brittany Travis ,  Crystal Monteiro ,  Sean Nolan ,  Rishon Saftler ,  John P. Virtue, Jr. ,  Stephen A. Sarcich

IPC: F02C6/08 ,  F02C9/18 ,  F04D29/52 ,  F04D29/64 ,  F04D27/02

CPC classification number: F02C6/08 ,  F02C9/18 ,  F04D27/0207 ,  F04D27/0215 ,  F04D27/023 ,  F04D29/526 ,  F04D29/644 ,  Y10T29/49236

Abstract: A disclosed gas turbine engine includes a case for a case for a compressor section including a bleed air slot. The bleed air slot includes an inlet having a first area radially inward of an outlet having a second area with the second area being greater than the first area. The bleed air slot further includes a center portion disposed along a radial line extending from an axis of the engine and an elongated portion extending from the opening at an angle relative to a line normal to the radial line.

公开(公告)号：US20150354457A1

公开(公告)日：2015-12-10

申请号：US14762092

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Philip Robert Rioux ,  Rishon Saftler

IPC: F02C7/18 ,  F01D25/24 ,  F02C6/08

CPC classification number: F02C7/18 ,  F01D25/243 ,  F01D25/246 ,  F02C6/08 ,  F05D2240/12 ,  Y10T29/49828

Abstract: A splitter for protecting parts of a gas turbine engine is provided. The splitter segregates the flow of hot and cold gases into the air bleed manifold around the high compressor section to reduce maximum temperatures and minimize the temperature gradients of engine parts, especially inner case flanges The splitter divides the air bleed manifold into an annular inner cavity and an outer cavity. The splitter directs relatively cold air from the high compressor bleed ducts into the inner cavity and relatively hot air from the aft hub into the outer cavity, away from the inner case flanges.

Abstract translation: 提供了用于保护燃气涡轮发动机的部件的分离器。 分流器将热和冷气体的流动分离成围绕高压缩机部分的排气歧管，以降低最大温度并使发动机部件，特别是内壳法兰的温度梯度最小化。分流器将排气歧管分成环形内腔， 外腔。 分离器将相对较冷的空气从高压缩机排放管道引导到内腔中，并将相对热的空气从后轮毂引导到外腔中，远离内壳法兰。

公开(公告)号：US20140096536A1

公开(公告)日：2014-04-10

申请号：US13646822

申请日：2012-10-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brittany Travis ,  Crystal Monteiro ,  Sean Nolan ,  Rishon Saftler ,  John P. Virtue, JR. ,  Stephen A. Sarcich

IPC: F02C6/08 ,  B23P17/00 ,  F04D29/52

CPC classification number: F02C6/08 ,  F02C9/18 ,  F04D27/0207 ,  F04D27/0215 ,  F04D27/023 ,  F04D29/526 ,  F04D29/644 ,  Y10T29/49236

Abstract: A disclosed gas turbine engine includes a case for a case for a compressor section including a bleed air slot. The bleed air slot includes an inlet having a first area radially inward of an outlet having a second area with the second area being greater than the first area. The bleed air slot further includes a center portion disposed along a radial line extending from an axis of the engine and an elongated portion extending from the opening at an angle relative to a line normal to the radial line.

Abstract translation: 所公开的燃气涡轮发动机包括用于包括排气槽的压缩机部分的壳体的壳体。 放气空气狭槽包括入口，入口具有出口的径向向内的第一区域，其具有第二区域，第二区域大于第一区域。 排放空气狭槽还包括沿着从发动机的轴线延伸的径向线设置的中心部分和从开口以相对于径向线垂直的线成一定角度延伸的细长部分。