公开(公告)号：US10982624B2

公开(公告)日：2021-04-20

申请号：US15943100

申请日：2018-04-02

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian Merry ,  Christopher M. Dye

IPC: F02C7/20 ,  F02K3/06 ,  F02C7/36

Abstract: A turbine engine is disclosed that includes a fan case surrounding a fan rotatable about an axis. A core is supported relative to the fan case by support structure arranged downstream from the fan. The core includes a core housing having an inlet case arranged to receive airflow from the fan. A compressor case is arranged axially adjacent to the inlet case and surrounds a compressor stage having a rotor blade with a blade trailing edge. The support structure includes a support structure leading edge facing the fan and a support structure trailing edge on a side opposite the support structure leading edge. The support structure trailing edge is arranged axially forward of the blade trailing edge. In one example, a forward attachment extends from the support structure to the inlet case.

公开(公告)号：US11518525B2

公开(公告)日：2022-12-06

申请号：US17411529

申请日：2021-08-25

Applicant: Raytheon Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian Merry ,  Stephen H. Taylor ,  Charles E. Lents

IPC: F02C6/08 ,  B64D13/08 ,  F02C9/18 ,  F02K3/115 ,  B64D27/10 ,  F01D15/10 ,  F02C3/04 ,  F02K3/06 ,  H02K7/18 ,  F02C7/18 ,  F02K3/04 ,  B64D13/06

Abstract: An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.

公开(公告)号：US20220018312A1

公开(公告)日：2022-01-20

申请号：US17217831

申请日：2021-03-30

Applicant: Raytheon Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian Merry ,  Christopher M. Dye

IPC: F02K3/06 ,  F02C7/36 ,  F02C7/20

Abstract: A turbine engine is disclosed that includes a fan case surrounding a fan rotatable about an axis. A core is supported relative to the fan case by support structure arranged downstream from the fan. The core includes a core housing having an inlet case arranged to receive airflow from the fan. A compressor case is arranged axially adjacent to the inlet case and surrounds a compressor stage having a rotor blade with a blade trailing edge. The support structure includes a support structure leading edge facing the fan and a support structure trailing edge on a side opposite the support structure leading edge. The support structure trailing edge is arranged axially forward of the blade trailing edge. In one example, a forward attachment extends from the support structure to the inlet case.

公开(公告)号：US20210285380A1

公开(公告)日：2021-09-16

申请号：US17195848

申请日：2021-03-09

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Hung Duong ,  Jonathan F. Zimmitti ,  William G. Sheridan ,  Michael E. McCune ,  Brian Merry

IPC: F02C7/32 ,  F02C3/06 ,  F02C7/18 ,  F02C7/36 ,  F02C7/268 ,  F01D15/10 ,  F01D25/12 ,  F16H1/22 ,  H02K7/116 ,  H02K7/18 ,  F01D15/12 ,  F02C7/275

Abstract: An exemplary gas turbine engine assembly includes a fan section including a fan, a first spool having a first turbine operatively mounted to a first turbine shaft, and a second spool having a second turbine operatively mounted to a second turbine shaft. The first and second towershafts are respectively coupled to the first and second turbine shafts. An accessory drive gearbox includes a set of gears. A compressor is driven by the first towershaft. A transmission couples a starter generator assembly to the set of gears. The transmission is transitionable between a first mode where the starter generator assembly is driven at a first speed relative to the second towershaft in response to rotation of the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft in response to rotation of the second towershaft.

公开(公告)号：US11408372B2

公开(公告)日：2022-08-09

申请号：US17217831

申请日：2021-03-30

Applicant: Raytheon Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian Merry ,  Christopher M. Dye

IPC: F02C7/20 ,  F02K3/06 ,  F02C7/36

Abstract: A turbine engine is disclosed that includes a fan case surrounding a fan rotatable about an axis. A core is supported relative to the fan case by support structure arranged downstream from the fan. The core includes a core housing having an inlet case arranged to receive airflow from the fan. A compressor case is arranged axially adjacent to the inlet case and surrounds a compressor stage having a rotor blade with a blade trailing edge. The support structure includes a support structure leading edge facing the fan and a support structure trailing edge on a side opposite the support structure leading edge. The support structure trailing edge is arranged axially forward of the blade trailing edge. In one example, a forward attachment extends from the support structure to the inlet case.

公开(公告)号：US20210380260A1

公开(公告)日：2021-12-09

申请号：US17411529

申请日：2021-08-25

Applicant: Raytheon Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian Merry ,  Stephen H. Taylor ,  Charles E. Lents

IPC: B64D13/08 ,  F02C6/08 ,  F02C9/18 ,  F02K3/115 ,  B64D27/10 ,  F01D15/10 ,  F02C3/04 ,  F02K3/06 ,  H02K7/18 ,  F02C7/18 ,  F02K3/04

Abstract: An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.