公开(公告)号：US10458266B2

公开(公告)日：2019-10-29

申请号：US15490304

申请日：2017-04-18

Applicant: United Technologies Corporation

Inventor： Daniel Carlson ,  Jonathan Ortiz ,  Matthew A. Devore ,  Raymond Surace

IPC: F01D5/08 ,  F01D11/04 ,  F01D5/06 ,  F01D9/04 ,  F01D11/00

Abstract: Gas turbine engines and turbines thereof including a stator section having a plurality of vanes, a rotating section having a plurality of blades, the rotating section being axially adjacent the stator section along an axis of the turbine, the stator section being aftward of the rotating section along the axis of the turbine, and a primary tangential onboard injector located radially inward from the stator section and configured to direct an airflow from the stator section in a forward direction toward the rotating section, the primary tangential onboard injector turning the airflow in a direction of rotation of the rotating section.

公开(公告)号：US20180334966A1

公开(公告)日：2018-11-22

申请号：US15601563

申请日：2017-05-22

Applicant: United Technologies Corporation

Inventor： Jonathan Ortiz ,  William K. Ackermann ,  Matthew P. Forcier

IPC: F02C9/18 ,  F02C7/18 ,  F01D9/06

CPC classification number: F02C9/18 ,  F01D9/065 ,  F02C6/08 ,  F02C7/18 ,  F05D2260/20 ,  F05D2260/50 ,  F05D2270/3015

Abstract: A bleed air cooling system for a gas turbine engine includes one or more bleed flowpaths operably connected to a bleed outlet to divert a bleed airflow from a gas turbine engine flowpath. Each bleed flowpath includes two or more bleed ports to divert a bleed airflow from a gas turbine engine flowpath, a bleed duct configured to convey the bleed airflow from the two or more bleed ports to the bleed outlet, and a delta-pressure valve located at each bleed port of the two or more bleed ports configured to move between an opened position and a closed position in response to a difference between a first pressure upstream of the delta-pressure valve and a second pressure downstream of the delta pressure valve. The bleed airflow is selectably conveyed through a bleed port of the two or more bleed ports depending on the operation of the associated delta-pressure valve.

公开(公告)号：US20180334962A1

公开(公告)日：2018-11-22

申请号：US15601499

申请日：2017-05-22

Applicant: United Technologies Corporation

Inventor： Jonathan Ortiz ,  William K. Ackermann ,  Matthew P. Forcier

IPC: F02C7/18

CPC classification number: F02C7/18 ,  F01P2023/00 ,  F01P2025/04 ,  F01P2025/08 ,  F02C6/08 ,  F02C7/057 ,  F02C9/18 ,  F05D2270/301 ,  F05D2270/303 ,  F16K31/00

Abstract: A bleed air cooling system for a gas turbine engine includes a bleed port located at an axial location of the gas turbine engine to divert a bleed airflow from a gas turbine engine flowpath, a bleed outlet located at a cooling location of the gas turbine engine and a bleed duct in fluid communication with the bleed port and the configured to convey the bleed airflow from the bleed port to the bleed outlet. A modulating valve is located at the bleed duct and is movable between a fully open position and a fully closed position to regulate the bleed airflow through the bleed duct based on one or more operating conditions of the gas turbine engine.

公开(公告)号：US20180291762A1

公开(公告)日：2018-10-11

申请号：US15484168

申请日：2017-04-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Ortiz ,  Lane Mikal Thornton ,  Matthew A. Devore

IPC: F01D25/12 ,  F02C3/04 ,  F01D17/10 ,  F01D17/16 ,  F01D9/04 ,  F01D11/14

CPC classification number: F01D25/12 ,  F01D5/081 ,  F01D9/041 ,  F01D9/065 ,  F01D11/14 ,  F01D17/105 ,  F01D17/162 ,  F02C3/04 ,  F02C6/08 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/35 ,  F05D2260/213 ,  F05D2300/50212 ,  Y02T50/676

Abstract: A gas turbine engine comprises a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine first stage blade having an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap taps air having been compressed by the compressor, the tapped air being passed through a heat exchanger. A vane section has vanes downstream of the combustor, but upstream of the first stage blade, and the air downstream of the heat exchanger passes radially inwardly of the combustor, along an axial length of the combustor, and then radially outwardly through a hollow chamber in the vanes, and then across the blade outer air seal, to cool the blade outer air seal.

公开(公告)号：US20180291744A1

公开(公告)日：2018-10-11

申请号：US15483752

申请日：2017-04-10

Applicant: United Technologies Corporation

Inventor： Matthew A Devore ,  Jonathan Ortiz

IPC: F01D5/08 ,  F01D5/18

CPC classification number: F01D5/081 ,  F01D5/082 ,  F01D5/187 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/81 ,  F05D2260/14 ,  F05D2260/201 ,  Y02T50/676

Abstract: An airfoil may comprise a root and an airfoil body radially outward of the root. The airfoil body may define a first cooling chamber and a second cooling chamber. A first passage may be defined within the root and configured to direct a first airflow radially outward through the root into the first cooling chamber. A second passage may be defined within the root and configured to direct a second airflow radially outward through the root and into the second cooling chamber.

公开(公告)号：US20180283195A1

公开(公告)日：2018-10-04

申请号：US15475656

申请日：2017-03-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Ortiz ,  Raymond Surace ,  Renee J. Jurek ,  Tracy A. Propheter-Hinckley

IPC: F01D11/20 ,  F02C3/04 ,  F01D5/02 ,  F02C9/18 ,  F04D29/54

CPC classification number: F01D11/20 ,  F01D5/02 ,  F01D9/065 ,  F01D11/24 ,  F02C3/04 ,  F02C9/18 ,  F04D29/542 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213 ,  F05D2300/50212 ,  Y02T50/676

Abstract: A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.

公开(公告)号：US20180202307A1

公开(公告)日：2018-07-19

申请号：US15405957

申请日：2017-01-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Ortiz

IPC: F01D11/24 ,  F02C7/18

Abstract: A clearance control system for a gas turbine engine comprises a blade outer air seal mounted on a carrier. At least one blade is rotatable about an engine axis. The blade outer air seal is spaced radially outwardly from a tip of the blade by a clearance. A heat exchanger is configured to deliver air at a first temperature to the blade outer air seal at a first operating condition to allow the blade outer air seal to move in a first direction to maintain a desired clearance, and configured to deliver air at a second temperature to the blade outer air seal at a second operating condition to allow the blade outer air seal to move in a second direction to maintain a desired clearance, and wherein the second temperature is less than the first temperature. A gas turbine engine and a method of controlling tip clearance in a gas turbine engine are also disclosed.