公开(公告)号：US11781506B2

公开(公告)日：2023-10-10

申请号：US16891492

申请日：2020-06-03

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan

IPC: F02K3/075 ,  F02K3/077 ,  F02K1/72 ,  F02K3/06 ,  F02C3/107 ,  F02K3/068 ,  F04D29/66 ,  F04D29/54 ,  F01D5/14

CPC classification number: F02K3/077 ,  F02K3/075 ,  F01D5/145 ,  F02K1/72 ,  F02K3/06 ,  F04D29/542 ,  F04D29/661

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：US20230235715A1

公开(公告)日：2023-07-27

申请号：US18130539

申请日：2023-04-04

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

CPC classification number: F02K3/06 ,  F02C3/107 ,  F02C7/36 ,  F02C7/20

Abstract: A turbofan engine includes a propulsor section that has a propulsor shaft in driving engagement with a propulsor. An epicyclic gear system has a gear mesh lateral stiffness and a gear mesh transverse stiffness. A gear system input 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 turbine section rotates at a first speed, and a second turbine rotates at a second speed that is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area of the first turbine, a second performance quantity is defined as the product of the second speed squared and the second area of the second turbine, and a performance quantity ratio is between 0.5 and 1.5.

公开(公告)号：US20230220784A1

公开(公告)日：2023-07-13

申请号：US18115943

申请日：2023-03-01

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Zubair Ahmed Baig ,  Gary Collopy ,  Coy Bruce Wood

IPC: F01D15/10 ,  F01D25/24 ,  F02C7/36 ,  F02C7/32 ,  F02K3/06 ,  B64D27/02

CPC classification number: F01D15/10 ,  F01D25/24 ,  F02C7/36 ,  F02C7/32 ,  F02K3/06 ,  F05D2220/76 ,  F05D2220/50 ,  B64D2027/026

Abstract: A turbine engine includes integrated electric machines in the compressor section and the turbine section to supplement power produced from fuel with electric power. The example compressor section includes a compressor electric motor that is coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to the geared architecture to supplement power driving the fan section. A turbine generator provides electric power to the turbine electric motor.

公开(公告)号：US20230182909A1

公开(公告)日：2023-06-15

申请号：US18103935

申请日：2023-01-31

Applicant: Raytheon Technologies Corporation

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

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

CPC classification number: B64D27/24 ,  B64D27/10 ,  F01D15/10 ,  F02C6/14 ,  F02C7/36 ,  H02K7/1823 ,  F05D2270/053 ,  B64D2221/00 ,  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：US11635043B2

公开(公告)日：2023-04-25

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 ,  F02C7/20 ,  F01D15/12 ,  F01D5/06 ,  F04D19/00 ,  F04D25/04 ,  F04D29/053 ,  F04D29/32 ,  F01D9/04

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：US20230037652A1

公开(公告)日：2023-02-09

申请号：US17393508

申请日：2021-08-04

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan ,  Christopher J. Hanlon

IPC: F02C3/10 ,  F02C7/36 ,  F02C6/02 ,  F01D13/00

Abstract: A gas turbine engine includes a fan positioned at an engine central longitudinal axis, and a fan drive turbine located at the engine central longitudinal axis and configured to drive rotation of the fan. A gas generator is non-coaxial with the fan drive turbine and operably connected to the fan drive turbine such that exhaust from the gas generator drives rotation of the fan drive turbine. An auxiliary power core is located at the engine central longitudinal axis, and one or more bleed passages connect the gas generator and the auxiliary power core. The one or more bleed passages are configured to selectably combine a bleed airflow from the gas generator and an auxiliary core airflow at the auxiliary power core to direct the combined airflow to the fan drive turbine to increase output of the fan drive turbine.

公开(公告)号：US20220205394A1

公开(公告)日：2022-06-30

申请号：US17492114

申请日：2021-10-01

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Coy Bruce Wood

IPC: F02C7/36 ,  F01D15/12 ,  F01D25/36 ,  F02C7/275 ,  F02K3/06 ,  F16H3/72 ,  H02K7/18 ,  H02K16/02

Abstract: A turbofan engine includes a first spool including a first turbine, and a first tower shaft engaged to the first spool. A second spool includes a second turbine, and a second tower shaft is engaged to the second spool. A superposition gearbox includes a sun gear, a plurality of intermediate gears engaged to the sun gear, and is supported in a carrier and a ring gear circumscribing the intermediate gears. The first tower shaft or the second tower shaft drives one of the intermediate gears. A drive motor is engaged to drive the sun gear, an inner electric motor, a stator disposed radially outside of the inner electric motor, and an outer electric motor disposed radially outside the stator. A first load on the first spool and a second load on the second spool is adjusted by operation of at least one of the inner electric motor and the outer electric motor.

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：US20210199056A1

公开(公告)日：2021-07-01

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

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：US12012896B2

公开(公告)日：2024-06-18

申请号：US17976254

申请日：2022-10-28

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis

IPC: F02C7/18 ,  F02C3/13 ,  F02C6/02

CPC classification number: F02C7/18 ,  F02C3/13 ,  F02C6/02 ,  F05D2220/329 ,  F05D2260/20

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.