公开(公告)号：US20210381431A1

公开(公告)日：2021-12-09

申请号：US16891492

申请日：2020-06-03

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan

IPC: F02C3/107 ,  F02C9/18 ,  F01D9/06 ,  F01D13/00 ,  F01D25/16 ,  F01D17/16

Abstract: A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor including a row of blades extending in a radial direction outwardly from a hub. The row of blades deliver flow to a bypass flow path, an intermediate flow path, and a core flow path. A first case surrounds the row of blades to establish the bypass flow path. A first flow splitter divides flow between the bypass flow path and a second duct. A row of guide vanes extends in the radial direction across the bypass flow path. A second flow splitter radially inboard of the first flow splitter divides flow from the second duct between the intermediate flow path and the core flow path. A bypass port interconnects the intermediate and bypass flow paths. A method of operation for a gas turbine engine is also disclosed.

公开(公告)号：US11193425B2

公开(公告)日：2021-12-07

申请号：US16445469

申请日：2019-06-19

Applicant: Raytheon Technologies Corporation

Inventor： Paul R. Hanrahan ,  Arthur M. Salve, Jr. ,  Daniel Bernard Kupratis

IPC: F02C7/36 ,  F02C7/32 ,  F02C6/08

Abstract: A turbine engine includes a core engine including a first spool and a second spool rotatable about a main engine longitudinal axis, a boost spool powered by a secondary drive system, and an accessory gearbox coupled to the core engine and the boost spool. A differential gear system is coupled between the core engine, the boost spool and the accessory gearbox for distributing power between the boost spool, the core engine and the accessory gearbox.

公开(公告)号：US11091272B2

公开(公告)日：2021-08-17

申请号：US16039849

申请日：2018-07-19

Applicant: Raytheon Technologies Corporation

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

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

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.

公开(公告)号：US20210164398A1

公开(公告)日：2021-06-03

申请号：US17176803

申请日：2021-02-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis

IPC: F02C7/18 ,  F02C6/02 ,  F02C3/13

Abstract: A multi-engine system includes a first gas turbine engine that includes a first compressor and a first turbine. The multi-engine system may further include a second gas turbine engine that has a second compressor and a second turbine. Still further, the multi-engine system may include a first crossover cooling network configured to route a first crossover airflow from the first compressor of the first gas turbine engine to the second turbine of the second gas turbine engine and a second crossover cooling network configured to route a second crossover airflow from the second compressor of the second gas turbine engine to the first turbine of the first gas turbine engine.

公开(公告)号：US10830153B2

公开(公告)日：2020-11-10

申请号：US16186811

申请日：2018-11-12

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

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

Abstract: A gas turbine engine turbine has a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, the high pressure turbine rotatable with the high pressure compressor as a high pressure spool in a first direction about an engine longitudinal axis, the low pressure turbine rotatable as a low pressure spool in the first direction about the engine longitudinal axis, a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, a fan section including a fan having a plurality of fan blades, the fan connected to the low pressure spool via a geared architecture such that the fan is rotatable about the engine longitudinal axis in a second direction opposed to the first direction, and a bypass ratio greater than 6.

公开(公告)号：US12071903B2

公开(公告)日：2024-08-27

申请号：US16864881

申请日：2020-05-01

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Martin Richard Amari ,  Geoffrey T. Blackwell

IPC: F02C9/18 ,  F02C7/26

CPC classification number: F02C9/18 ,  F02C7/26 ,  F05D2240/127 ,  F05D2260/606 ,  F05D2260/85

Abstract: A system for bleeding air from a core flow path of a gas turbine engine includes a bleed valve in a bleed air duct configured to receive bleed air from a first entrance point to the core flow path into the bleed air duct; a pressurized air valve in a pressurized air duct configured to receive pressurized air from a second entrance point to the core flow path, the pressurized air at a pressure greater than that received into the first entrance point; an eductor outlet from the pressurized air duct located in the bleed air duct; and a control system operable to control operation of the bleed valve and the pressurized air valve.

公开(公告)号：US11753990B2

公开(公告)日：2023-09-12

申请号：US17864982

申请日：2022-07-14

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan ,  Arthur M. Salve, Jr.

IPC: F02C3/113 ,  F02C3/14 ,  F02C9/56 ,  F02K3/10 ,  F02C9/00

CPC classification number: F02C3/113 ,  F02C3/14 ,  F02C9/56 ,  F02K3/10 ,  F02C9/00 ,  F05D2220/32

Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.

公开(公告)号：US20230212985A1

公开(公告)日：2023-07-06

申请号：US18115986

申请日：2023-03-01

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Neil J. Terwilliger ,  Michael M. Romero

IPC: F02C7/32 ,  F02C7/36

CPC classification number: F02C7/32 ,  F02C7/36 ,  F05D2260/40311 ,  F16H3/724

Abstract: A disclosed drive assembly for an auxiliary power unit includes a first drive shaft driven by an auxiliary power unit, a second drive shaft driven by a first electric motor, a differential gear system including a ring gear driven by the second drive shaft, a and planet gears supported within a carrier attached to the ring gear. The first drive shaft and an output shaft are coupled to the planet gears and a generator is driven by the output shaft. The electric motor and the auxiliary power unit combine to drive the output shaft.

公开(公告)号：US11608786B2

公开(公告)日：2023-03-21

申请号：US17730782

申请日：2022-04-27

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

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

Abstract: A gas turbine engine includes a propulsor section including a propulsor, a compressor section including a low pressure compressor and a high pressure compressor, a geared architecture, a turbine section including a low pressure turbine and a high pressure 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：US11598286B2

公开(公告)日：2023-03-07

申请号：US17538048

申请日：2021-11-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

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

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section, a compressor section including a low pressure compressor and a second compressor section, and a turbine section including a low pressure turbine and a high pressure turbine. The low pressure turbine drives the low pressure compressor and the gear arrangement to drive the propulsor. A core split power ratio is provided by power input to the high pressure compressor divided by a power input to the low pressure compressor measured in horsepower.