公开(公告)号：US11913349B2

公开(公告)日：2024-02-27

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 ,  F01D15/12 ,  F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  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：US11846238B2

公开(公告)日：2023-12-19

申请号：US17060171

申请日：2020-10-01

Applicant: Raytheon Technologies Corporation

Inventor： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F02C3/04 ,  F02K3/02 ,  F02C3/06

CPC classification number: F02C7/36 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A turbofan gas turbine engine includes, among other things, a fan section, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to 10. A gear arrangement drives the fan section. A compressor section includes a low pressure compressor section and a high pressure compressor section. A turbine section drives the gear arrangement. An overall pressure ratio is provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section, and greater than 40. The pressure ratio across the high pressure compressor section is between 7 and 15, and the pressure ratio across the low pressure compressor section is between 4 and 8.

公开(公告)号：US20230193830A1

公开(公告)日：2023-06-22

申请号：US18110454

申请日：2023-02-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Brian D. Merry ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F01D25/16 ,  F01D5/06 ,  F02C3/06 ,  F02C7/06 ,  F04D29/32

CPC classification number: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F01D25/162 ,  F01D5/06 ,  F02C3/06 ,  F02C7/06 ,  F04D29/321 ,  F04D29/325 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A gas turbine engine includes a compressor section including a first compressor, a turbine section including a first turbine and a second turbine, a first shaft and a second shaft, the first shaft interconnecting the first turbine and the second compressor, and a geared architecture. The first shaft is supported on a first bearing in an overhung manner. A performance ratio is between 0.5 and 1.5.

公开(公告)号：US11661906B2

公开(公告)日：2023-05-30

申请号：US17371672

申请日：2021-07-09

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Christopher A. Eckett ,  Gabriel L. Suciu

IPC: F02K3/075 ,  F02K1/72 ,  F02K3/06 ,  F02K1/76 ,  F02K1/09 ,  B64D27/26 ,  B64D29/06 ,  B64D33/04 ,  F01D25/24 ,  F02C3/04 ,  F02K1/70

CPC classification number: F02K3/075 ,  B64D27/26 ,  B64D29/06 ,  B64D33/04 ,  F01D25/24 ,  F02C3/04 ,  F02K1/09 ,  F02K1/72 ,  F02K1/763 ,  F02K3/06 ,  B64D2027/266 ,  B64D2027/268 ,  F02K1/70 ,  F05D2240/14 ,  F05D2270/051 ,  Y02T50/60

Abstract: An integrated propulsion system according to an example of the present disclosure includes, among other things, a fan section, a gas turbine engine, a geared architecture, a nacelle assembly and a mounting assembly. The nacelle assembly includes a fan nacelle and an aft nacelle, the fan nacelle arranged at least partially about a fan and the engine, and the fan nacelle arranged at least partially about a core cowling to define a bypass flow path.

公开(公告)号：US20220106912A1

公开(公告)日：2022-04-07

申请号：US17555606

申请日：2021-12-20

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

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

Abstract: An example gas turbine engine includes a propulsor assembly consisting of a fan module and a fan drive turbine module, an epicyclic gear train, a high spool and a low spool. A weight of the propulsor assembly is less than 40% of a total weight of a gas turbine engine. The high spool includes an outer shaft, a high pressure turbine and a high pressure compressor. The low spool includes an inner shaft, a low pressure turbine and a low pressure compressor. The inner shaft drives the propulsor through the gear train to drive the propulsor. A weight of the propulsor is greater than a weight of the low pressure turbine.

公开(公告)号：US11149650B2

公开(公告)日：2021-10-19

申请号：US16025038

申请日：2018-07-02

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 first compressor section and a second compressor, the second compressor section including a second compressor section inlet with a second compressor section inlet annulus area, a fan duct including a fan duct annulus area outboard of the second compressor section inlet, a shaft assembly having a first portion and a second portion, a turbine in fluid communication with the combustor, the turbine having a first turbine section coupled to the first portion of the shaft assembly to drive the first compressor section, and a second turbine section coupled to the second portion of the shaft assembly to drive the fan, an epicyclic transmission coupled to the fan and rotatable by the second turbine section through the second portion of the shaft assembly to allow the second turbine to turn faster than the fan, wherein the second 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 less than 0.6.

公开(公告)号：US20210301731A1

公开(公告)日：2021-09-30

申请号：US17230326

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

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including an array of fan blades rotatable about an engine axis, a compressor including a high pressure compressor section and a low pressure compressor section, the low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor inlet annulus area, a fan duct including a fan duct annulus area outboard of the low pressure compressor section inlet, and a turbine having a high pressure turbine section and a low pressure turbine section driving the fan through a speed reduction mechanism, wherein the low pressure turbine section defines a maximum gas path radius and the fan blades define a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.6.

公开(公告)号：US10823071B2

公开(公告)日：2020-11-03

申请号：US16158581

申请日：2018-10-12

Applicant: Raytheon Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/18 ,  F01D25/08 ,  F01D5/02 ,  F01D5/08 ,  F02C6/08 ,  F02C7/12 ,  F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine comprises a compressor section and a turbine section, with the turbine section having a first stage blade row and a downstream blade row. A higher pressure tap is tapped from a higher pressure first location in the compressor. A lower pressure tap is tapped from a lower pressure location in the compressor which is at a lower pressure than the first location. The higher pressure tap passes through a heat exchanger, and then is delivered to cool the first stage blade row in the turbine section. The lower pressure tap is delivered to at least partially cool the downstream blade row.

公开(公告)号：US10808933B2

公开(公告)日：2020-10-20

申请号：US16001349

申请日：2018-06-06

Applicant: Raytheon Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill

IPC: F23R3/10 ,  F02C3/04 ,  F01D5/08 ,  F01D9/06 ,  F01D25/12 ,  F02C6/08 ,  F02C7/18

Abstract: A turbine injection system for a gas turbine engine includes a first end operable to receive air from a heat exchanger, a second end operable to distribute mixed cooling air to a turbine stage, an opening downstream of said first end and a mixing plenum downstream of said first end and said opening. The opening provides a direct fluid pathway into said turbine injection system.

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.