公开(公告)号：US11846196B2

公开(公告)日：2023-12-19

申请号：US16797194

申请日：2020-02-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dmitriy B. Sidelkovskiy ,  Pitchaiah Vijay Chakka ,  Michael Winter ,  Daniel Bernard Kupratis ,  Nathan L. Messersmith

IPC: F01D15/10 ,  B64D27/10 ,  B64D27/24 ,  B64D41/00 ,  F01D15/12 ,  F02C6/06 ,  F02K3/065 ,  H02K7/116 ,  H02K7/18 ,  H02K7/20 ,  H02K11/00 ,  B64D27/02

CPC classification number: F01D15/10 ,  B64D27/10 ,  B64D27/24 ,  B64D41/00 ,  F01D15/12 ,  F02C6/06 ,  F02K3/065 ,  H02K7/116 ,  H02K7/1823 ,  H02K7/20 ,  H02K11/0094 ,  B64D2027/026 ,  F05D2220/50 ,  F05D2220/76

Abstract: An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.

公开(公告)号：US11299279B2

公开(公告)日：2022-04-12

申请号：US16361482

申请日：2019-03-22

Applicant: United Technologies Corporation

Inventor： Michael Winter

IPC: F02C7/141 ,  F02C7/16 ,  F02C9/18 ,  B64D13/08 ,  F25B9/14 ,  F25J3/04 ,  B01D45/08 ,  B01D53/00 ,  B03C1/28 ,  B64D27/12 ,  B64D33/08 ,  F01D15/00 ,  F01D25/12 ,  F02C6/08 ,  F02C7/143 ,  F02C7/18 ,  F02K3/06 ,  B64D13/06 ,  F17C7/02 ,  F17C7/04 ,  B64D37/32

Abstract: A system for an aircraft includes an engine bleed source of a gas turbine engine. The system also includes a means for chilling an engine bleed air flow from the engine bleed source to produce a chilled working fluid. The system further includes a means for providing the chilled working fluid for an aircraft use.

公开(公告)号：US20200325852A1

公开(公告)日：2020-10-15

申请号：US16837143

申请日：2020-04-01

Applicant: United Technologies Corporation

Inventor： Dmitriy B. Sidelkovskiy ,  Pitchaiah Vijay Chakka ,  Michael Winter ,  Daniel Bernard Kupratis

IPC: F02K3/06 ,  F04D29/32

Abstract: An after-fan system for a gas turbine engine includes a variable pitch fan exit guide vane array. An after-fan turbine downstream of the variable pitch fan exit guide vane array and a control operable to vary a pitch of the variable fan exit guide vane array. A method of generating thrust for a gas turbine engine includes rotating a fan section with an array of fan blades; rotating an after-fan turbine downstream of the fan section; and varying a pitch of a variable fan exit guide vane array downstream of the fan section and upstream of the after-fan turbine.

公开(公告)号：US20190292982A1

公开(公告)日：2019-09-26

申请号：US16361482

申请日：2019-03-22

Applicant: United Technologies Corporation

Inventor： Michael Winter

IPC: F02C6/08 ,  B64D33/08 ,  B64D27/12 ,  F01D15/00 ,  F01D25/12 ,  F02C9/18 ,  F02C7/18 ,  F02C7/143 ,  F02K3/06 ,  F25J3/04 ,  B01D53/00 ,  B01D45/08 ,  B03C1/28

Abstract: A system for an aircraft includes an engine bleed source of a gas turbine engine. The system also includes a means for chilling an engine bleed air flow from the engine bleed source to produce a chilled working fluid. The system further includes a means for providing the chilled working fluid for an aircraft use.

公开(公告)号：US20190291877A1

公开(公告)日：2019-09-26

申请号：US16360280

申请日：2019-03-21

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael Winter ,  Charles E. Lents ,  Nathan Snape ,  Alan H. Epstein

IPC: B64D13/08 ,  F02C7/16 ,  F02C7/141

Abstract: A cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for collecting liquid air. The first air cycle machine is operable to output a cooling air stream based on a first air source. The second air cycle machine is operable to output a chilled air stream at a cryogenic temperature based on a second air source cooled by the cooling air stream of the first air cycle machine. An output of the second air cycle machine is provided to the means for collecting liquid air.

公开(公告)号：US10309315B2

公开(公告)日：2019-06-04

申请号：US15083752

申请日：2016-03-29

Applicant: United Technologies Corporation

Inventor： Ashok K. Jain ,  Michael Winter

IPC: F02C7/262 ,  F02K1/12 ,  F02K1/15 ,  F02K3/075 ,  F01D25/24 ,  F02C9/16 ,  F02K1/06

Abstract: An example turbofan engine starting system includes a core nacelle housing a compressor and a turbine. The core nacelle is disposed within a fan nacelle. The fan nacelle includes a turbofan. A bypass flow path downstream from the turbofan is arranged between the two nacelles. A controller is programmed to manipulate the nozzle exit area to facilitate startup of the engine. In one example, manipulates the nozzle exit area using nozzles, in response to an engine shutdown condition. The nozzles open and close to adjust the nozzle exit area.

公开(公告)号：US09909495B2

公开(公告)日：2018-03-06

申请号：US14600487

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Wesley K. Lord ,  Jesse M. Chandler ,  Michael Winter ,  Michael E. McCune ,  William G. Sheridan

IPC: F02C3/10 ,  F02K3/00 ,  B64D27/12 ,  B64D35/04 ,  F02K3/077 ,  F02C3/107

CPC classification number: F02C3/10 ,  B64D27/12 ,  B64D35/04 ,  F02C3/107 ,  F02K3/00 ,  F02K3/077

Abstract: A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.

公开(公告)号：US20150361880A1

公开(公告)日：2015-12-17

申请号：US14600487

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Wesley K. Lord ,  Jesse M. Chandler ,  Michael Winter ,  Michael E. McCune ,  William G. Sheridan

IPC: F02C3/10 ,  F01D15/10

CPC classification number: F02C3/10 ,  B64D27/12 ,  B64D35/04 ,  F02C3/107 ,  F02K3/00 ,  F02K3/077

Abstract: A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.

Abstract translation: 燃气涡轮发动机包括多个风扇转子。 气体发生器包括至少一个压缩机转子，至少一个气体发生器涡轮机转子，燃烧部分和在至少一个气体发生器涡轮机转子下游的风扇驱动涡轮机。 轴构造成由风扇驱动涡轮机驱动。 轴接合齿轮以驱动多个风扇转子。 系统控制提供给多个风扇转子的功率量。 还公开了一种操作燃气涡轮发动机的方法。

公开(公告)号：US12042881B2

公开(公告)日：2024-07-23

申请号：US16220415

申请日：2018-12-14

Applicant: United Technologies Corporation

Inventor： Michael Winter

IPC: B23K26/384 ,  B23K26/382 ,  B23K101/00 ,  B23P15/02 ,  F01D5/18 ,  G02B3/00 ,  G02B6/04 ,  G02B6/10

CPC classification number: B23K26/384 ,  B23K26/389 ,  B23P15/02 ,  F01D5/186 ,  G02B3/00 ,  G02B6/04 ,  G02B6/10 ,  B23K2101/001 ,  B23P2700/06 ,  F05D2230/13 ,  F05D2260/202 ,  G02B2003/0093

Abstract: A laser hole drilling system includes a laser source that generates a laser beam along an optical axis; a spherical lens along the optical axis downstream of the laser source; and a control system in communication with the spherical lens and the laser source, the control system operable to locate the spherical lens with respect to the laser source to produce a light distribution in polar coordinates of a real portion of the Fourier Transform to generate an asymmetric teardrop shaped energy distribution at a focal plane.

公开(公告)号：US11994089B2

公开(公告)日：2024-05-28

申请号：US16837143

申请日：2020-04-01

Applicant: United Technologies Corporation

Inventor： Dmitriy B. Sidelkovskiy ,  Pitchaiah Vijay Chakka ,  Michael Winter ,  Daniel Bernard Kupratis

IPC: F02K3/06 ,  F04D29/32 ,  F01D17/16 ,  F02C7/36

CPC classification number: F02K3/06 ,  F04D29/323 ,  F01D17/162 ,  F02C7/36 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2260/40311 ,  F05D2260/74 ,  F05D2260/79

Abstract: An after-fan system for a gas turbine engine includes a variable pitch fan exit guide vane array. An after-fan turbine downstream of the variable pitch fan exit guide vane array and a control operable to vary a pitch of the variable fan exit guide vane array. A method of generating thrust for a gas turbine engine includes rotating a fan section with an array of fan blades; rotating an after-fan turbine downstream of the fan section; and varying a pitch of a variable fan exit guide vane array downstream of the fan section and upstream of the after-fan turbine.