公开(公告)号：US20240337187A1

公开(公告)日：2024-10-10

申请号：US18130872

申请日：2023-04-04

Applicant: Raytheon Technologies Corporation

Inventor： William K. Ackermann ,  Brian F. Hilbert ,  Paul A. Sicard ,  Andrew E. Breault ,  Rishon Saftler

IPC: F02C9/18 ,  F02C3/06

CPC classification number: F01D5/081 ,  F01D5/082 ,  F02C9/18 ,  F02C3/06 ,  F02C7/18 ,  F05D2260/606

Abstract: A gas turbine engine is provided that includes a high pressure compressor (HPC), a combustor section, a high pressure turbine (HPT), and a bypass tangential on board injector (TOBI) system. The combustor section has a combustor. A core gas path extends through the HPC, the combustor section, and the HPT. The bypass TOBI system extends circumferentially around the engine axial centerline, and has a plurality of nozzles, inner and outer radial sides, a plurality of first type and second type radial passages configured to allow the gas from the HPC to pass from the inner radial side of the bypass TOBI system to the outer radial side of the bypass TOBI system, wherein the first type radial passages are differently configured from the second type radial passages.

公开(公告)号：US11486314B2

公开(公告)日：2022-11-01

申请号：US17020034

申请日：2020-09-14

Applicant: Raytheon Technologies Corporation

Inventor： Gabriel L. Suciu ,  William K. Ackermann ,  Harold W. Hipsky

IPC: F02C9/00 ,  F02C9/18 ,  F02C3/04 ,  F02C7/06 ,  F02C7/32 ,  B64D13/06 ,  F02C6/08

Abstract: An environmental control system for an aircraft includes a higher pressure tap associated with a higher compression location in a main compressor section. The higher pressure tap leads into a turbine section of a turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive a compressor section of the turbocompressor. A combined outlet receives airflow from a turbine outlet and a compressor outlet intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft system. A buffer air outlet communicates airflow to an engine buffer air system.

公开(公告)号：US10794275B2

公开(公告)日：2020-10-06

申请号：US15794175

申请日：2017-10-26

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jorn A. Glahn ,  William K. Ackermann ,  Clifton J. Crawley ,  Philip S. Stripinis

IPC: F02C6/08 ,  F01D25/18 ,  F02C7/14 ,  F02C7/12

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft and first and second bearing structures that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains the lubricant within the bearing compartments. A buffer system is configured to pressurize the seals to prevent the lubricant from escaping the bearing compartments. The buffer system includes a first circuit configured to supply a first buffer supply air to the first bearing structure, a second circuit configured to supply a second buffer supply air to the second bearing structure, and a controller configured to select between at least two bleed air supplies to communicate the first buffer supply air and the second buffer supply air.

公开(公告)号：US20240410587A1

公开(公告)日：2024-12-12

申请号：US18208113

申请日：2023-06-09

Applicant: Raytheon Technologies Corporation

Inventor： William K. Ackermann ,  Andrew E. Breault ,  Thomas E. Clark ,  Daniel B. Kupratis

IPC: F02C7/22

Abstract: A gas turbine engine having an axial centerline is provided that includes compressor, combustor, and turbine sections, a tangential on board injector (TOBI) system, and an HPC leakage guide structure. The compressor section has a high pressure compressor (HPC) that includes an HPC aft hub. The TOBI system extends circumferentially around the engine axial centerline, and has a plurality of nozzles and an inner radial flange. The HPC leakage guide structure has forward and aft ends. The forward end is disposed and configured to receive a leakage flow from the HPC and the aft end is engaged with the TOBI inner radial flange. The HPC leakage guide structure and the HPC aft hub define an HPC aft hub cavity. The HPC aft hub cavity extends between the forward and aft ends and has a flow area that is non-decreasing in a direction from the forward end to the aft end.

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：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：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：US20250027422A1

公开(公告)日：2025-01-23

申请号：US18224908

申请日：2023-07-21

Applicant: Raytheon Technologies Corporation

Inventor： Andrew E. Breault ,  William K. Ackermann

IPC: F02C6/08 ,  F02C7/06

Abstract: A buffer air assembly for an aircraft engine includes a low-pressure header, a high-pressure header, a low-pressure bleed air source, a high-pressure bleed air source, and an electric buffer compressor. The low-pressure header is connected to at least one low-pressure bearing compartment. The high-pressure header is connected to at least one high-pressure bearing compartment. The low-pressure bleed air source is connected to the low-pressure header. The low-pressure bleed air source is configured to direct a low-pressure buffering air to the at least one low-pressure bearing compartment through the low-pressure header. The high-pressure bleed air source is configured to direct a high-pressure buffering air to the at least one high-pressure bearing compartment through the high-pressure header. The electric buffer compressor is connected to the low-pressure header and the high-pressure header. The electric buffer compressor is configured to direct pressurized buffering air to the low-pressure header and the high-pressure header.

公开(公告)号：US20210317785A1

公开(公告)日：2021-10-14

申请号：US16844683

申请日：2020-04-09

Applicant: Raytheon Technologies Corporation

Inventor： Enzo DiBenedetto ,  Anthony R. Bifulco ,  William K. Ackermann ,  Paul E. Coderre ,  John H. Mosley ,  Stephen K. Kramer

IPC: F02C7/18 ,  F01D25/12

Abstract: A cooling system includes an inlet, a passageway, and a feed passage. The inlet is defined by a strut of a diffuser case that extends between a first case portion and a second case portion. The inlet extends from a leading surface towards a trailing surface along a first axis. The passageway is defined by the strut and extends from the inlet towards the second case portion along a second axis that is disposed transverse to the first axis. The feed passage is defined between a body of a tangential onboard injection system that extends between and is connected to an inner vane platform of a guide vane and the second case portion. The feed passage extends along an axis that is disposed parallel to the first axis.

公开(公告)号：US20250027445A1

公开(公告)日：2025-01-23

申请号：US18224921

申请日：2023-07-21

Applicant: Raytheon Technologies Corporation

Inventor： Andrew E. Breault ,  William K. Ackermann

IPC: F02C6/08 ,  F02C9/18

Abstract: A buffer air assembly for an aircraft engine includes a first pressurized air header, at least one first bearing compartment, a first bleed air source, and at least one electric buffer compressor. The at least one first bearing compartment is connected in fluid communication with the first pressurized air header. The first bleed air source is connected in fluid communication with the first pressurized air header by a first bleed check valve. The first bleed air source is configured to direct first pressurized bleed air to the first pressurized air header through the first bleed check valve. The at least one electric buffer compressor is connected in fluid communication with the first pressurized air header by a first buffer compressor check valve.