公开(公告)号：US20190153866A1

公开(公告)日：2019-05-23

申请号：US15819047

申请日：2017-11-21

Applicant: United Technologies Corporation

Inventor： Dmytro Mykolayovych Voytovych ,  Alexander Staroselsky ,  Om P. Sharma ,  Gabriel L. Suciu ,  Brian Merry ,  Ioannis Alvanos

IPC: F01D5/02 ,  F01D5/22 ,  F04D29/32 ,  F01D5/34

Abstract: An exemplary gas turbine engine includes a turbine section and a fan mechanically connected to the turbine section such that rotation of the turbine drives rotation of the fan. The fan includes a hub, a plurality of blade bodies extending radially outward from the hub to a first partial shroud, and a plurality of blade tips extending radially outward from the partial shroud.

公开(公告)号：US20190003391A1

公开(公告)日：2019-01-03

申请号：US16111870

申请日：2018-08-24

Applicant: United Technologies Corporation

Inventor： Nathan Snape ,  James D. Hill ,  Gabriel L. Suciu ,  Brian Merry

IPC: F02C7/14

Abstract: An aircraft thermal management system includes a first fluid system containing a first fluid, a fluid loop containing a thermally neutral heat transfer fluid, a second fluid system containing a second fluid, a first heat exchanger configured to transfer heat from the first fluid to the thermally neutral heat transfer fluid, and a second heat exchanger configured to transfer heat from the thermally neutral heat transfer fluid to the second fluid. The fluid loop is configured to provide the thermally neutral heat transfer fluid to the first heat exchanger at a pressure that matches the pressure of the first fluid.

公开(公告)号：US20180320541A1

公开(公告)日：2018-11-08

申请号：US15588911

申请日：2017-05-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Mark F. Zelesky ,  Brian Merry ,  Gabriel L. Suciu

IPC: F01D11/20 ,  F01D25/24

Abstract: A control system for a gas turbine engine comprises a case structure, a clearance control ring mounted for movement relative to the case structure, an outer air seal mounted to the clearance control ring and facing a first engine component, and a control and valve assembly that receives flow from a flow input source. The control and valve assembly is configured to direct flow into a first cavity positioned radially between the case structure and the outer air seal, and wherein the control and valve assembly is configured to direct flow into a second cavity positioned downstream of the first cavity to interact with a second engine component. A method of controlling flow between a compressor section and turbine section is also disclosed.

公开(公告)号：US20180313274A1

公开(公告)日：2018-11-01

申请号：US15498764

申请日：2017-04-27

Applicant: United Technologies Corporation

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

IPC: F02C7/36

CPC classification number: F02C7/36 ,  F02C7/32 ,  F05D2250/322 ,  F05D2260/40311

Abstract: A gas turbine engine comprises a high speed spool and a low speed spool. A low speed power takeoff is driven by the low speed spool and a high speed power takeoff is driven by the high speed spool. The low speed power takeoff drives a plurality of low speed driven accessories about low speed spool drive axes and the high speed power takeoff drives a plurality of high speed driven accessories about high speed spool drive axes. The low speed spool drive axes are generally tangential to an envelope defined about a center axis of the engine, and the high speed spool drive axes are generally tangential to an envelope defined about the center.

公开(公告)号：US10107127B2

公开(公告)日：2018-10-23

申请号：US14793468

申请日：2015-07-07

Applicant: United Technologies Corporation

Inventor： James Hill ,  Brian Merry ,  Gabriel Suciu

IPC: F01D11/04 ,  F01D5/06 ,  F01D5/22 ,  F01D5/24 ,  F01D11/00 ,  F01D5/18

Abstract: A gas turbine engine including an axial high pressure compressor having expansion slots in the outer rim of the rotor section. The expansion slots may be positioned between blades of a rotor segment. The fore end of the slots may have an axial seal which is coupled to the inner surface of the outer rim in the first rotor segment, and may comprise a fin configuration. The axial seal may be integral to the inner surface of the outer rim. The compressor may comprise a plurality of expansion slots and axial seals, including in a plurality of rotor segments.

公开(公告)号：US20180291818A1

公开(公告)日：2018-10-11

申请号：US15484841

申请日：2017-04-11

Applicant: United Technologies Corporation

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

IPC: F02C7/32 ,  F16H1/22

Abstract: An assembly is provided for a gas turbine engine with an axial centerline. This assembly includes a gearbox, a first torque transmission apparatus and a second torque transmission apparatus. The gearbox includes a plurality of first gears and a plurality of second gears. The first gears are meshed together and respectively rotatable about parallel first gear axes. The second gears are meshed together and respectively rotatable about parallel second gear axes. Each of the first gear axes and each of the second gear axes is non-parallel with the axial centerline. The first torque transmission apparatus is configured to drive the first gears. The second torque transmission apparatus is configured to drive the second gears.

公开(公告)号：US20180291817A1

公开(公告)日：2018-10-11

申请号：US15484376

申请日：2017-04-11

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

CPC classification number: F02C7/32 ,  F02C7/185 ,  F02C7/36 ,  F05D2220/764 ,  F05D2220/768 ,  F05D2270/023

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：US20180223693A1

公开(公告)日：2018-08-09

申请号：US15424930

申请日：2017-02-06

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian Merry ,  Ioannis Alvanos

IPC: F01D25/30 ,  F02K1/04 ,  F02K3/06

CPC classification number: F01D25/30 ,  F01D9/02 ,  F02C3/04 ,  F02K1/04 ,  F02K1/48 ,  F02K3/06 ,  F05D2240/14 ,  F05D2260/96 ,  F05D2300/6033 ,  Y02T50/672

Abstract: A turbine exhaust assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a turbine exhaust case comprised of CMC material and attachable to a turbine case, a tail cone comprised of CMC material that has a leading edge and a trailing edge, and an exhaust mixer comprised of CMC material and coupled to the turbine exhaust case. The exhaust mixer has a plurality of lobes arranged about the tail cone to define an exhaust flow path. A plurality of struts extend from the tail cone to support the exhaust mixer at a location aft of the leading edge of the tail cone. A method of assembling a propulsion system is also disclosed.

公开(公告)号：US20180187602A1

公开(公告)日：2018-07-05

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 ,  F02K3/06

CPC classification number: F02C7/143 ,  F02C6/08 ,  F02C7/185 ,  F02C7/32 ,  F02C9/18 ,  F02K3/06 ,  F05D2220/3218 ,  F05D2220/323 ,  F05D2260/211 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/676

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：US20180162537A1

公开(公告)日：2018-06-14

申请号：US15665860

申请日：2017-08-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu ,  Brian Merry ,  Charles E. Lents ,  Stephen H. Taylor

IPC: B64D13/08 ,  F02C6/08 ,  F02K3/06 ,  F02C3/04 ,  F02C9/18 ,  F01D15/10 ,  H02K7/18 ,  B64D27/10

Abstract: An aircraft has a gas turbine engine including a compressor section that includes at least one compressor bleed. An environmental control system has an air input configured to receive pressurized cabin air. An intercooler has an input and an output. A selection valve is configured to selectively connect the bleeds to an intercooler input. At least one auxiliary compressor is connected to the intercooler output. An output of at least one auxiliary compressors is connected to an ECS air input. A controller is configured to receive contemporaneous operational data, calculate minimum configuration requirements to satisfy environmental demands, and transmit calculated configuration requirements to at least the selection valve to achieve a desired pressure and temperature for the air downstream of the auxiliary compressor. A method for supplying engine air to an environmental control system and a system for use on a turbine engine powered aircraft are also disclosed.