公开(公告)号：US20250154881A1

公开(公告)日：2025-05-15

申请号：US19024324

申请日：2025-01-16

Applicant: RTX CORPORATION

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F01D25/24 ,  F01D5/02 ,  F01D5/12 ,  F01D17/10 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F04D29/32 ,  F16H1/28

Abstract: A gas turbine engine includes a propulsor section including a propulsor hub, the hub including a hub diameter supporting a plurality of propulsor blades, a compressor section including a first compressor and a second compressor aft of the first compressor relative to an engine longitudinal axis, and a turbine section including a first turbine and a second turbine. A geared architecture that interconnects the first turbine and the propulsor hub such that the fan hub is rotatable at a lower relative speed than the first turbine. A compressor inlet passage is disposed annularly about the geared architecture.

公开(公告)号：US12179929B2

公开(公告)日：2024-12-31

申请号：US18215394

申请日：2023-06-28

Applicant: RTX CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

IPC: B64D27/40 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/24 ,  F01D25/28 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02C9/18 ,  F02C9/20 ,  F02K1/15 ,  F02K3/06

Abstract: A gas turbine engine includes, among other things, a propulsor section including a rotor and blades, a gear train, a compressor section and a turbine section. A static structure includes a first case and a second case. The first case includes a first engine mount location. The second case includes a second engine mount location. The first engine mount location is axially near the gear train.

公开(公告)号：US12044183B2

公开(公告)日：2024-07-23

申请号：US18197863

申请日：2023-05-16

Applicant: RTX CORPORATION

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C3/10 ,  F02C3/107 ,  F02C3/113 ,  F02C3/20 ,  F02C6/20 ,  F02C7/20 ,  F02C7/32

CPC classification number: F02C7/36 ,  F02C3/10 ,  F02C3/107 ,  F02C7/20 ,  F02C7/32 ,  F02C3/113 ,  F02C3/20 ,  F02C6/20 ,  F02C6/206 ,  F05D2220/36 ,  F05D2260/40311 ,  Y02T50/60 ,  Y10T29/49321

Abstract: An example gas turbine engine includes a propulsor assembly consisting of a propulsor and a first turbine. An epicyclic gear train defines a gear reduction ratio of greater than 2.3. A weight of the propulsor assembly is less than 40 percent of a total weight of the gas turbine engine, excluding any nacelle. A first spool includes a first shaft that connects a first compressor and the first turbine. The first shaft drives the propulsor through the gear train to drive the propulsor at a lower speed than the first spool. A second spool includes a second shaft connecting a second compressor and a second turbine. A weight of the propulsor is greater than a weight of the first turbine.

公开(公告)号：US20240076999A1

公开(公告)日：2024-03-07

申请号：US18505408

申请日：2023-11-09

Applicant: RTX CORPORATION

Inventor： Frederick M. Schwarz ,  Nathan Snape

IPC: F01D25/08

CPC classification number: F01D25/08 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2300/614

Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap. A flowpath is defined between a rotating surface and a non-rotating surface. The flowpath is connected downstream of the heat exchanger and is configured to deliver air to at least one of the plurality of rotating components. At least a portion of the non-rotating surface and the rotating surface includes a base metal. An insulation material is disposed on a surface along the flowpath.

公开(公告)号：US12247493B2

公开(公告)日：2025-03-11

申请号：US17969179

申请日：2022-10-19

Applicant: RTX CORPORATION

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C7/36 ,  F01D5/02 ,  F01D5/12 ,  F01D17/10 ,  F01D25/24 ,  F02C3/107 ,  F02K3/06 ,  F04D29/32 ,  F16H1/28

Abstract: A gas turbine engine includes, among other things, a propulsor section including a propulsor hub, the hub including a hub diameter supporting a plurality of propulsor blades. A compressor section includes a first compressor and a second compressor. A turbine section includes a first turbine and a second turbine. A geared architecture interconnects the first turbine and the propulsor hub. The geared architecture includes a gear volume. A compressor inlet passage is disposed annularly about the geared architecture.

公开(公告)号：US20240401500A1

公开(公告)日：2024-12-05

申请号：US18420862

申请日：2024-01-24

Applicant: RTX CORPORATION

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

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

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, propulsor means, first compression means, second compression means, reduction means for reducing a rotational speed of an output that drives the propulsor means relative to an input, first expansion means, and second expansion means. The reduction means includes an epicyclic gear system with a gear reduction. The gear system is straddle-mounted by first and second bearings on opposite sides of the gear reduction relative to an engine longitudinal axis.

公开(公告)号：US11970984B2

公开(公告)日：2024-04-30

申请号：US18107126

申请日：2023-02-08

Applicant: RTX CORPORATION

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

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

CPC classification number: F02C7/36 ,  F01D1/26 ,  F01D15/12 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/40311 ,  F05D2270/051

Abstract: A gas turbine engine includes a propulsor section including a propulsor, a compressor section including a first compressor and a second compressor, a geared architecture, a turbine section including a first turbine and a drive turbine, and a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, wherein the power density is a ratio of a thrust provided by the engine to a volume of the turbine section.

公开(公告)号：US11920485B2

公开(公告)日：2024-03-05

申请号：US17887869

申请日：2022-08-15

Applicant: RTX Corporation

Inventor： Frederick M. Schwarz ,  Nathan Snape

IPC: F01D25/08

CPC classification number: F01D25/08 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2300/614

Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap. A flowpath is defined between a rotating surface and a non-rotating surface. The flowpath is connected downstream of the heat exchanger and is configured to deliver air to at least one of the plurality of rotating components. At least a portion of the non-rotating surface and the rotating surface includes a base metal. An insulation material is disposed on a surface along the flowpath.

公开(公告)号：US11859538B2

公开(公告)日：2024-01-02

申请号：US18096872

申请日：2023-01-13

Applicant: RTX CORPORATION

Inventor： Frederick M. Schwarz

IPC: F02C3/107 ,  F01D5/14 ,  F02K3/06

CPC classification number: F02C3/107 ,  F01D5/142 ,  F02K3/06 ,  F05D2220/327 ,  F05D2220/36 ,  F05D2260/40311 ,  Y02T50/60

Abstract: A turbine engine includes a first compression section includes a last blade trailing edge radial tip length that is greater than about 67% of the radial tip length of a leading edge of a first stage of the first compression section. A second compression section includes a last blade trailing edge radial tip length that is greater than about 57% of a radial tip length of a leading edge of a first stage of the first compression section.

公开(公告)号：US12258135B2

公开(公告)日：2025-03-25

申请号：US18103935

申请日：2023-01-31

Applicant: RTX CORPORATION

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz ,  William G. Sheridan ,  Glenn Levasseur

IPC: F02C6/14 ,  B64D27/10 ,  B64D27/24 ,  F01D15/10 ,  F02C7/36 ,  H02K7/18 ,  B64D27/02 ,  F02C3/107 ,  F02C6/02

Abstract: An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.