公开(公告)号：US11319831B2

公开(公告)日：2022-05-03

申请号：US17145766

申请日：2021-01-11

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

IPC: F16H57/04 ,  F01D15/12 ,  F01D25/18 ,  F01D25/16 ,  F01D1/02 ,  F01D5/02 ,  F02C7/32 ,  F16H57/08 ,  F02C7/36 ,  F02K3/06

Abstract: A turbine engine according to an example of the present disclosure includes, among other things, a fan shaft, at least one tapered bearing mounted on the fan shaft, the fan shaft including at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing, a fan mounted for rotation on the at least one tapered bearing. An epicyclic gear train is coupled to drive the fan, the epicyclic gear train including a carrier supporting intermediate gears that mesh with a sun gear, and a ring gear surrounding and meshing with the intermediate gears, wherein the epicyclic gear train defines a gear reduction ratio of greater than or equal to 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train, the turbine section having a fan drive turbine that includes a pressure ratio that is greater than 5. The fan includes a pressure ratio that is less than 1.45, and the fan has a bypass ratio of greater than ten (10).

公开(公告)号：US20220074350A1

公开(公告)日：2022-03-10

申请号：US17527542

申请日：2021-11-16

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C7/36 ,  F02K3/06

Abstract: A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the plurality of planet gears. A carrier supports the plurality of planet gears. The geared architecture includes a power transfer parameter (PTP) defined as power transferred through the geared architecture divided by gear volume multiplied by a gear reduction ratio.

公开(公告)号：US20210324758A1

公开(公告)日：2021-10-21

申请号：US17359894

申请日：2021-06-28

Applicant: Raytheon Technologies Corporation

Inventor： Subhradeep Chowdhury ,  David M. Bostwick ,  David Gelwan ,  Frederick M. Schwarz

IPC: F01D19/02 ,  F02C9/00 ,  B64D27/12 ,  B64D41/00 ,  B64F1/36 ,  F01D25/34 ,  F02C3/04 ,  F02C6/20 ,  F02C7/277

Abstract: A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.

公开(公告)号：US20210301730A1

公开(公告)日：2021-09-30

申请号：US17230271

申请日：2021-04-14

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C3/107 ,  F02C9/18 ,  F01D11/12 ,  F01D5/06 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D19/02 ,  F02K3/075 ,  F02K3/06 ,  F04D29/32 ,  F04D29/54

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including a circumferential array of fan blades, a compressor in fluid communication with the fan, the compressor including a low pressure compressor section and a high pressure compressor section, the low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor section inlet annulus area, a fan duct including a fan duct annulus area outboard of the a low pressure compressor section inlet, a turbine in fluid communication with the combustor, the turbine having a high pressure turbine section and a low pressure turbine that drives the fan, a speed reduction mechanism coupled to the fan and rotatable by the low pressure turbine section to allow the low pressure turbine section to turn faster than the fan, wherein the low pressure turbine section includes a maximum gas path radius and the fan blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is between 0.50 and 0.55, or is greater than 0.55 and less than or equal to 0.65.

公开(公告)号：US20210293154A1

公开(公告)日：2021-09-23

申请号：US17337658

申请日：2021-06-03

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F01D25/24 ,  F02K3/06 ,  F16H1/28 ,  F02C3/107 ,  F01D5/02 ,  F01D5/12 ,  F01D17/10 ,  F04D29/32

Abstract: A turbofan gas turbine engine includes, among other things, a fan section including a fan hub and an outer housing, the fan hub including a hub diameter supporting a plurality of fan blades, a turbine section including a fan drive turbine, and a geared architecture that interconnects the fan drive turbine and the fan hub, the geared architecture including a gear volume.

公开(公告)号：US11053843B2

公开(公告)日：2021-07-06

申请号：US16158545

申请日：2018-10-12

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

IPC: F02C7/36 ,  F02C3/107 ,  F01D25/16 ,  F02K3/06

Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction.

公开(公告)号：US20210139155A1

公开(公告)日：2021-05-13

申请号：US17028578

申请日：2020-09-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Nigel David Sawyers-Abbott ,  Frederick M. Schwarz

IPC: B64D27/26 ,  F02C7/20 ,  F01D25/28 ,  F02K3/06

Abstract: A turbofan engine may comprise an inlet and a fan case coupled to the inlet. An engine case may be coupled to the fan case via a vane extending between the fan case and the engine case. A strut apparatus may extend from the fan case and limit deflection of the fan case. The strut apparatus may comprise a first end proximate the fan case, and a second end coupled to at least one of the engine case or a structure for mounting the turbofan engine to an aircraft.

公开(公告)号：US20210062724A1

公开(公告)日：2021-03-04

申请号：US17037916

申请日：2020-09-30

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F01D1/26 ,  F01D15/12

Abstract: A turbofan gas turbine engine includes a fan section having a fan, a compressor section including a low pressure compressor and a high pressure compressor, a geared architecture including an epicyclic gear train, a turbine section including a low pressure turbine and a high pressure turbine, the fan driven by the low pressure turbine through the geared architecture, and a power density between 4.84 lbf/in3 and 5.5 lbf/in3.

公开(公告)号：US20210040898A1

公开(公告)日：2021-02-11

申请号：US16881567

申请日：2020-05-22

Applicant: Raytheon Technologies Corporation

Inventor： Paul R. Adams ,  Frederick M. Schwarz ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Gabriel L. Suciu

IPC: F02C9/18 ,  F02C3/04 ,  F02C7/20 ,  F01D1/02 ,  F01D5/02 ,  F01D9/04 ,  F01D25/24 ,  F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F02C3/113 ,  F02K3/02 ,  F02K3/075 ,  F02K7/06

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

公开(公告)号：US10907579B2

公开(公告)日：2021-02-02

申请号：US16736013

申请日：2020-01-07

Applicant: Raytheon Technologies Corporation

Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

IPC: F02K3/06 ,  F02C7/36 ,  F16H57/04

Abstract: A gas turbine engine includes a bypass ratio greater than about ten (10). A fan is supported on a fan shaft and has a plurality of fan blades. A gear system is connected to the fan shaft and a plurality of planetary gears. A first set of opposed angled ring gear teeth are separated from a second set of opposed angled ring gear teeth. A lubricant flow path is located axially between the first set of opposed angled ring gear teeth and the second set of opposed angled ring gear teeth. An annular channel axially is aligned with the lubricant flow path. A low pressure turbine has an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1. A low fan pressure ratio is less than 1.45 across the fan blade alone.