公开(公告)号：US11215143B2

公开(公告)日：2022-01-04

申请号：US16684968

申请日：2019-11-15

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 fan section, and a compressor section including a low pressure compressor and a second compressor section, and a turbine section including a fan drive turbine and a high pressure turbine. The fan drive turbine drives the low pressure compressor and a gear arrangement to drive the fan section. 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.

公开(公告)号：US11168617B2

公开(公告)日：2021-11-09

申请号：US16261688

申请日：2019-01-30

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：US20210339880A1

公开(公告)日：2021-11-04

申请号：US17376675

申请日：2021-07-15

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

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：US11125155B2

公开(公告)日：2021-09-21

申请号：US16291241

申请日：2019-03-04

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

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

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan having a plurality of fan blades, and a nacelle surrounding the plurality of fan blades, a compressor section including a low pressure compressor and a high pressure compressor, the low pressure compressor including a plurality of stages, and the high pressure compressor including 6 or more stages. A turbine section includes a fan drive turbine that drives the fan section through a gear arrangement, and including a second turbine that drives the high pressure compressor. A power ratio is provided by the combination of a first power input of the low pressure compressor and a second power input of the high pressure compressor, the power ratio defined by the second power input divided by the first power input, and the power ratio is less than or equal to 1.0.

公开(公告)号：US11047337B2

公开(公告)日：2021-06-29

申请号：US15485512

申请日：2017-04-12

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 gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with defined flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is between 0.5 and 1.5.

公开(公告)号：US20210071585A1

公开(公告)日：2021-03-11

申请号：US17012600

申请日：2020-09-04

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Coy Bruce Wood ,  Ramesh Rajagopalan ,  Zubair Ahmed Baig

IPC: F02C7/36 ,  B64D27/02 ,  B64D35/02 ,  F02C6/14

Abstract: A gas turbine engine includes a generator that is configured to be driven by a turbine section, an electric motor that is configured to receive at least a portion of electric power from the generator, a gearbox that is mechanically coupled to both the electric motor and the generator, and a control system that has an operational amplifier that is configured to synchronize operation of the electric motor and the generator. The operational amplifier electrically couples the electric motor to the generator and is configured to define an electrical gain that matches a mechanical gain that is defined by the gearbox.

公开(公告)号：US20210054809A1

公开(公告)日：2021-02-25

申请号：US16999408

申请日：2020-08-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Mark Tu ,  Paul R. Hanrahan ,  Arthur M. Salve, JR.

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

Abstract: A gas turbine engine is disclosed. In various embodiments, the gas turbine engine includes a high pressure turbine having a first stage and a second stage, 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; a high pressure compressor connected to a high pressure compressor spool; and a 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 connected to the high pressure compressor spool.

公开(公告)号：US12098646B2

公开(公告)日：2024-09-24

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 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  B64D27/02

CPC classification number: F01D15/10 ,  F01D25/24 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  B64D27/026 ,  F05D2220/50 ,  F05D2220/76

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：US11952947B2

公开(公告)日：2024-04-09

申请号：US17493002

申请日：2021-10-04

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Christopher J. Hanlon ,  William G Sheridan

IPC: F02C7/36 ,  F02C6/00 ,  F02C9/00 ,  F02K3/06 ,  F16H1/28 ,  H02K7/116 ,  H02K7/14 ,  H02K7/18

CPC classification number: F02C7/36 ,  F02C6/00 ,  F02C9/00 ,  F02K3/06 ,  F16H1/28 ,  H02K7/116 ,  H02K7/14 ,  H02K7/1823 ,  F05D2220/323 ,  F05D2220/70 ,  F05D2260/40311 ,  F05D2270/02 ,  F05D2270/051 ,  F05D2270/101 ,  F05D2270/20

Abstract: A disclosed gas turbine engine includes a first electric motor assembly that provides a first drive input for driving fan blades about an axis. A geared architecture is driven by a turbine section and is coupled to the fan section to provide a second drive input for driving the fan blades. A second electric motor assembly is coupled to rotate the geared architecture relative to a fixed structure for controlling a speed of the fan blades provided by a combination of the first drive input and the second drive input.

公开(公告)号：US20230383699A1

公开(公告)日：2023-11-30

申请号：US18107126

申请日：2023-02-08

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

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

CPC classification number: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F01D1/26 ,  F01D15/12 ,  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.