公开(公告)号：US10753286B2

公开(公告)日：2020-08-25

申请号：US16152710

申请日：2018-10-05

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C3/107 ,  F02C7/20 ,  F02C7/32 ,  F02C3/10

Abstract: An example gas turbine engine includes a propulsor assembly including a fan and a fan drive turbine. A weight of the propulsor assembly is less than about 40% of a total weight of the gas turbine engine.

公开(公告)号：US10731560B2

公开(公告)日：2020-08-04

申请号：US15907942

申请日：2018-02-28

Applicant: United Technologies Corporation

Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Brian Merry ,  Jesse M. Chandler ,  Frederick M. Schwarz

IPC: F02C7/143 ,  F02C6/08 ,  F02C7/18 ,  F02C9/18 ,  F02C7/32 ,  F02K3/06

Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap and configured to deliver air to an aircraft fuselage. A cooling compressor is connected downstream of the heat exchanger. A high pressure feed is configured to deliver air at a second pressure which is higher than the first pressure. The cooling compressor is configured to deliver air to at least one of the plurality of rotating components. A valve assembly that can select whether air from the first tap or air from the high pressure feed is delivered to the aircraft pneumatic system.

公开(公告)号：US10704468B2

公开(公告)日：2020-07-07

申请号：US14771069

申请日：2014-02-28

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/18 ,  F02C6/08 ,  F01D9/06 ,  F01D17/10 ,  F01D9/04 ,  F02C7/06 ,  F02C7/14 ,  F01D5/02 ,  F02C3/04 ,  F02C7/04 ,  F01D25/24 ,  F04D29/54 ,  F01D25/12

Abstract: A gas turbine engine is provided comprising a compressor section, a combustor section, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said compressor section.

公开(公告)号：US10605173B2

公开(公告)日：2020-03-31

申请号：US16456087

申请日：2019-06-28

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Hung Duong ,  Jonathan F. Zimmitti ,  William G. Sheridan ,  Michael E. McCune ,  Brian Merry

IPC: F02C7/32 ,  F02C7/18 ,  F02C7/36

Abstract: A gas turbine engine comprises a low speed spool and a high speed spool, with each of the spools including a turbine to drive a respective one of the spools. The high speed spool rotates at a higher speed than the low speed spool. A high speed power takeoff is driven to rotate by the high speed spool, and a low speed power takeoff is driven to rotate by the low speed spool. The high speed power takeoff drives a starter generator and a permanent magnet alternator. The low speed power takeoff drives a variable frequency generator.

公开(公告)号：US10590853B2

公开(公告)日：2020-03-17

申请号：US15409974

申请日：2017-01-19

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Hung Duong ,  Jonathan F. Zimmitti ,  William G. Sheridan ,  Michael E. McCune ,  Brian Merry

IPC: F02C7/32 ,  F02C7/277 ,  F02C7/22 ,  F01D15/10 ,  F01D15/08 ,  F01D15/12 ,  F01D5/06 ,  F01D25/20 ,  F01D25/16 ,  F02C7/36 ,  F01D5/02 ,  F02C7/06

Abstract: A gas turbine engine assembly includes a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, first and second towershafts respectively coupled to the first and second turbine shafts, an accessory drive gearbox mounted to the engine static structure, a hydraulic pump, and a transmission. The transmission is transitionable between a first mode where the hydraulic pump is driven at a first speed relative to a first towershaft, a second mode where the hydraulic pump is driven at a different, second speed relative to the first towershaft, and a third mode where the hydraulic pump is driven at a different, third speed relative to the first towershaft.

公开(公告)号：US10549845B2

公开(公告)日：2020-02-04

申请号：US15606051

申请日：2017-05-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Alan H. Epstein ,  Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64C21/06 ,  B64C23/02 ,  B64C1/00 ,  B64D33/02

Abstract: A propulsion system for an aircraft including at least two main gas turbine engines and a plurality of dedicated boundary layer ingestion fans. The propulsion system is arranged such that a combined thrust produced by the boundary layer ingestion fans is less than 20 percent of a total thrust of the main engines and the boundary layer ingestion fans. The boundary layer ingestion fans are controllable and selectively turned off at lower speeds.

公开(公告)号：US20200025147A1

公开(公告)日：2020-01-23

申请号：US16254889

申请日：2019-01-23

Applicant: United Technologies Corporation

Inventor： Christopher A. Eckett ,  Gabriel L. Suciu

IPC: F02K3/075 ,  F02K1/72 ,  F02K3/06 ,  B64D27/26 ,  B64D29/06 ,  B64D33/04 ,  F01D25/24 ,  F02C3/04 ,  F02K1/76 ,  F02K1/09

Abstract: An integrated propulsion system according to an example of the present disclosure includes, among other things, components that include a gas turbine engine, a nacelle assembly and a mounting assembly, the system designed by a process comprising identifying two or more of internal structural loading requirements, external structural mount loading requirements, aerodynamic requirements, and acoustic requirements for the system, and interdependently designing said components to meet said requirements. The nacelle assembly includes a fan nacelle and an aft nacelle, the fan nacelle arranged at least partially about a fan and the engine, and the fan nacelle arranged at least partially about a core cowling to define a bypass flow path.

公开(公告)号：US10519869B2

公开(公告)日：2019-12-31

申请号：US15137614

申请日：2016-04-25

Applicant: United Technologies Corporation

Inventor： Paul Attridge ,  Gabriel L. Suciu ,  Kurt J. Sobanski ,  Jesse M. Chandler

IPC: F02C7/32 ,  F02C7/20 ,  B64C27/64 ,  B64C27/625 ,  F02C7/36 ,  B64C27/68 ,  B64C33/00 ,  H02K11/20 ,  F02C3/04 ,  F02K3/06 ,  H02K7/00 ,  F02C7/25

Abstract: An electromechanical system for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine, and an electrical motor located at a second side of the firewall and configured to drive the mechanical component. The electrical motor mechanically connected to the mechanical component through a firewall opening in the firewall, the first side having a higher operating temperature than the second side. An electrical connection extends between the mechanical component and the electrical motor via the same firewall opening.

公开(公告)号：US10472081B2

公开(公告)日：2019-11-12

申请号：US15874335

申请日：2018-01-18

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Wesley K. Lord

IPC: B64D35/08 ,  B64C11/00 ,  B64C21/06 ,  B64C39/00 ,  B64C1/06 ,  B64D35/02 ,  B64C23/02 ,  B64C5/02 ,  F04D17/04 ,  B64D27/02 ,  B64D41/00

Abstract: A cross flow fan to be incorporated into an aircraft fuselage comprises an ingestion fan rotor to be positioned in a tail section of an aircraft fuselage to reduce boundary layer air from a top surface of the fuselage and to drive the air away from the top surface, and a drive arrangement for the ingestion fan rotor. An aircraft is also disclosed.

公开(公告)号：US20190316526A1

公开(公告)日：2019-10-17

申请号：US16456087

申请日：2019-06-28

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Hung Duong ,  Jonathan F. Zimmitti ,  William G. Sheridan ,  Michael E. McCune ,  Brian Merry

IPC: F02C7/32 ,  F02C7/36 ,  F02C7/18

Abstract: A gas turbine engine comprises a low speed spool and a high speed spool, with each of the spools including a turbine to drive a respective one of the spools. The high speed spool rotates at a higher speed than the low speed spool. A high speed power takeoff is driven to rotate by the high speed spool, and a low speed power takeoff is driven to rotate by the low speed spool. The high speed power takeoff drives a starter generator and a permanent magnet alternator. The low speed power takeoff drives a variable frequency generator.