公开(公告)号：US11131207B1

公开(公告)日：2021-09-28

申请号：US16864765

申请日：2020-05-01

Applicant: Raytheon Technologies Corporation

Inventor： John R. Farris ,  Michael G. McCaffrey

IPC: F01D11/22

Abstract: A semi-autonomous rapid response active clearance control system for a gas turbine engine includes an outer case, a carrier for a blade outer airseal positioned radially inward of the outer case, a blade outer airseal positioned radially inward of and mounted to the carrier, at least one electromechanical actuator attached to the outer case and selectively operable to move the carrier, and a sensing system. The sensing system includes a maneuver sensor housed within the actuator and configured to output a first signal, a position sensor mounted proximate to the blade outer airseal and configured to output a second signal, and a control means in communication with the maneuver sensor and the position sensor.

公开(公告)号：US20210148289A1

公开(公告)日：2021-05-20

申请号：US17159525

申请日：2021-01-27

Applicant: Raytheon Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Michael G. McCaffrey

IPC: F02C9/18 ,  F02C7/143 ,  F02C7/32 ,  F02C7/18 ,  F01D17/10 ,  F01D25/12 ,  F02C7/36 ,  F04D29/28

Abstract: A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions.

公开(公告)号：US10920611B2

公开(公告)日：2021-02-16

申请号：US16897433

申请日：2020-06-10

Applicant: Raytheon Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D25/12 ,  F01D1/02 ,  F01D5/08 ,  F01D11/00 ,  F01D11/02 ,  F02C7/18

Abstract: An on-board injector that delivers discharge air toward a turbine rotor of a gas turbine engine includes a second wall spaced form a first wall to define an annular inlet about an engine longitudinal axis and a multiple of airfoil shapes between the first wall and the second wall to segregate discharge air from the annular inlet, and a multiple of bypass apertures each along a radial axis transverse to the engine longitudinal axis through each of the multiple of airfoil shapes and the respective first wall, the second wall.

公开(公告)号：US20210025285A1

公开(公告)日：2021-01-28

申请号：US17066865

申请日：2020-10-09

Applicant: Raytheon Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D11/08 ,  F01D25/24 ,  F01D25/28

Abstract: A blade outer air seal (BOAS) includes a tube of a ceramic matrix composite (CMC) material. A preform within the shell defines a mount for the BOAS. The preform is of a CMC material. A gas turbine engine and a method of forming a blade outer air seal (BOAS) are also disclosed.