公开(公告)号：US11203982B2

公开(公告)日：2021-12-21

申请号：US16436569

申请日：2019-06-10

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 and is between 219 and 328.

公开(公告)号：US11149644B2

公开(公告)日：2021-10-19

申请号：US16360329

申请日：2019-03-21

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  John T. Schmitz

IPC: F02C7/18 ,  B64D33/12 ,  F02C7/12 ,  F02K3/077 ,  B64D33/10 ,  F01D25/14 ,  B64D33/08 ,  F01D25/08 ,  F02C7/14 ,  F02C7/32 ,  F02K3/105 ,  F02K3/115 ,  B64D33/02 ,  F28D21/00

Abstract: A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.

公开(公告)号：US20210301765A1

公开(公告)日：2021-09-30

申请号：US17342100

申请日：2021-06-08

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Jason Husband ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann

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

Abstract: A turbofan engine includes a fan section that drives air along a bypass flow path in a bypass duct. An epicyclic gear system in driving engagement with the fan shaft and has a gear mesh lateral stiffness and a gear mesh transverse stiffness. A gear system input to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness. A first performance quantity is defined as the product of a first speed squared and a first area and a second performance quantity is defined as the product of a second speed squared and a second area. A performance quantity ratio of a first performance quantity to a second performance quantity is between 0.5 and 1.5.

公开(公告)号：US20210231025A1

公开(公告)日：2021-07-29

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: F01D15/12 ,  F01D25/18 ,  F01D25/16 ,  F01D1/02 ,  F01D5/02 ,  F02C7/32 ,  F16H57/04

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：US10975715B2

公开(公告)日：2021-04-13

申请号：US16123027

申请日：2018-09-06

Applicant: Raytheon Technologies Corporation

Inventor： William K. Ackermann ,  Clifton J. Crawley, Jr. ,  Frederick M. Schwarz

IPC: F01D11/02 ,  F01D5/30 ,  F01D5/08 ,  F01D9/06 ,  F01D11/00 ,  F16J15/44 ,  F01D9/04 ,  F01D11/12

Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a first bladed rotor assembly, a second bladed rotor assembly, a stator vane assembly, a stator structure and a seal assembly. The second bladed rotor assembly includes a rotor disk structure. The stator vane assembly is axially between the first and the second bladed rotor assemblies. The stator structure is mated with and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.

公开(公告)号：US11674411B2

公开(公告)日：2023-06-13

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

CPC classification number: F01D19/02 ,  B64D27/12 ,  B64D41/00 ,  B64F1/364 ,  F01D25/34 ,  F02C3/04 ,  F02C6/20 ,  F02C7/277 ,  F02C9/00 ,  B64D2041/002 ,  F05D2220/323 ,  F05D2220/50 ,  F05D2260/85 ,  F05D2270/303

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：US20230175433A1

公开(公告)日：2023-06-08

申请号：US17897870

申请日：2022-08-29

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

IPC: F02C3/04 ,  F02K3/075 ,  F01D25/24 ,  F01D25/16 ,  F01D25/28 ,  F02K3/06 ,  F01D9/02

CPC classification number: F02C3/04 ,  F02K3/075 ,  F01D25/24 ,  F01D25/162 ,  F01D25/28 ,  F02K3/06 ,  F01D9/023 ,  F05D2240/12 ,  F05D2240/24 ,  Y02T50/60

Abstract: A gas turbine engine includes a propulsor. A speed reduction device is drivingly connected to the propulsor. A compressor section with a high pressure compressor has between 8 and 13 stages and a pressure ratio of at least 16:1 and less than 35:1. A turbine section including a transition duct is located between a high pressure turbine and a low pressure turbine including fewer support struts than vanes in a first vane row of the low pressure turbine. The first vane row of the low pressure turbine is located downstream of the transition duct and downstream of a first row of blades in the low pressure turbine. The first row of blades in the low pressure turbine are immediately downstream of the support struts.

公开(公告)号：US20230167752A1

公开(公告)日：2023-06-01

申请号：US18104375

申请日：2023-02-01

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu ,  William K. Ackermann ,  Daniel Bernard Kupratis ,  Michael E. McCune

IPC: F01D25/16 ,  F02K3/06 ,  F02C3/107 ,  F01D15/12 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36

CPC classification number: F01D25/164 ,  F02K3/06 ,  F02C3/107 ,  F01D15/12 ,  F01D25/162 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, first and second bearings, and a fan drive shaft interconnecting the gear system and the fan. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

公开(公告)号：US20230160337A1

公开(公告)日：2023-05-25

申请号：US17898728

申请日：2022-08-30

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

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

CPC classification number: F02C3/107 ,  F01D25/16 ,  F02K3/06 ,  F02C7/36 ,  F05D2260/40 ,  F05D2260/40311 ,  F05D2220/327

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：US11578651B2

公开(公告)日：2023-02-14

申请号：US17383512

申请日：2021-07-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

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

Abstract: A propulsor section includes a propulsor having a plurality of blades rotatable about an engine longitudinal axis. A compressor section includes a low pressure compressor and a high pressure compressor. A turbine section includes a low pressure turbine that drives the propulsor through an epicyclic gear arrangement, and includes a second turbine that drives the high pressure compressor. A power ratio is provided by the combination of a first power input of the low pressure compressor and a second power input of the high pressure compressor. The power ratio is defined by the second power input divided by the first power input. The power ratio is equal to, or greater than, 1.0 and less than, or equal to, 1.4.