公开(公告)号：US20210239074A1

公开(公告)日：2021-08-05

申请号：US17213725

申请日：2021-03-26

Applicant: Raytheon Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Karl L. Hasel

IPC: F02K3/00 ,  F02C7/36 ,  F01D25/16 ,  F02K3/04 ,  F02C7/06 ,  F02C3/04

Abstract: A gas turbine engine includes a shaft and a hub supported by the shaft. A housing includes an inlet and an intermediate case that respectively provide an inlet and an intermediate case flow path. A rotor is connected to the hub and supports a compressor section arranged axially between the inlet and the intermediate case flow paths. A compressor section inlet has a radially inner boundary that is spaced a second radial distance from the rotational axis different from the first radial distance. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. An inner race of the first bearing and an inner race of the second bearing engage and rotate with the hub. A fan shaft is drivingly connected to a fan having fan blades. A gear system is connected to the fan shaft and driven through a flex shaft.

公开(公告)号：US11512651B2

公开(公告)日：2022-11-29

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

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：US11215197B2

公开(公告)日：2022-01-04

申请号：US16251133

申请日：2019-01-18

Applicant: Raytheon Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Brian D. Merry

IPC: F04D29/58 ,  F02C6/08 ,  F02C3/13 ,  F02C7/18 ,  F02C9/18 ,  F01D25/12 ,  F02C7/143

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

公开(公告)号：US11149689B2

公开(公告)日：2021-10-19

申请号：US16152502

申请日：2018-10-05

Applicant: Raytheon Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Karl L. Hasel

IPC: F02C7/36 ,  F02K3/00 ,  F01D25/16 ,  F02K3/04 ,  F02C7/06 ,  F02C3/04

Abstract: A gas turbine engine includes a housing includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A rotor is connected to the hub and supports a compressor section. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. The radially inner boundary of the core inlet is at a location of a core inlet stator and the radially inner boundary of the compressor section inlet is at a location of the first stage low-pressure compressor rotor.

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：US10815888B2

公开(公告)日：2020-10-27

申请号：US15943825

申请日：2018-04-03

Applicant: Raytheon Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu

IPC: F01D25/16 ,  F02C7/06

Abstract: A geared turbofan gas turbine engine includes a fan section and a core section. The core section includes a compressor section, a combustor section and a turbine section. The fan section includes a gearbox and a fan. A low spool includes a low turbine within the turbine section and a forward connection to a gearbox for driving the fan. The low spool is supported for rotation about the axis at a forward most position by a forward roller bearing and at an aft position by a thrust bearing.