公开(公告)号：US20180363492A1

公开(公告)日：2018-12-20

申请号：US16059377

申请日：2018-08-09

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Federico Papa

IPC: F01D17/14 ,  F02C3/04 ,  F02C9/18 ,  F02C7/18 ,  F01D25/26

Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.

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：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：US10094278B2

公开(公告)日：2018-10-09

申请号：US14892103

申请日：2014-05-06

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C3/107 ,  F16C35/06 ,  F02C7/06 ,  F02C7/36 ,  F01D25/16 ,  F02C3/06 ,  F02K3/06 ,  F16C19/26 ,  F16C19/54 ,  F16C19/55

Abstract: A turbofan engine (20) comprises a fan (28). A fan drive gear system (60) is configured to drive the fan. A low spool comprises a low pressure turbine (50) and a low shaft (56) coupling the low pressure turbine to the fan drive gear system. An intermediate spool comprises an intermediate pressure turbine (48), a compressor (42), and an intermediate spool shaft (54) coupling the intermediate pressure turbine to the intermediate spool compressor. A combustor (45) is between a core spool compressor (44) and a high pressure turbine (46). A first (160) main bearing engages a static support (164; 164′) and a forward hub (236) of the intermediate spool. A second (162) main bearing engages the low shaft and the forward hub.

公开(公告)号：US10082034B2

公开(公告)日：2018-09-25

申请号：US14755952

申请日：2015-06-30

Applicant: United Technologies Corporation

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

IPC: F01D5/34 ,  F01D5/22 ,  F01D5/02

CPC classification number: F01D5/225 ,  B23P15/006 ,  F01D5/02 ,  F01D5/10 ,  F01D5/34 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2260/941

Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, adjacent ones of the plurality of blades are joined by a flexible web.

公开(公告)号：US10072569B2

公开(公告)日：2018-09-11

申请号：US14806809

申请日：2015-07-23

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Nathan Snape ,  Christopher M. Dye

IPC: F02C7/12 ,  F02C3/04 ,  F02C7/06 ,  F01D25/18 ,  F02C7/32 ,  F01D25/12 ,  F02C7/14

CPC classification number: F02C3/04 ,  F01D25/12 ,  F01D25/18 ,  F02C7/06 ,  F02C7/12 ,  F02C7/14 ,  F02C7/32

Abstract: A gas turbine engine includes an engine static structure housing that includes a compressor section and a turbine section. A combustor section is arranged axially between the compressor section and the turbine section. A core nacelle encloses the engine static structure to provide a core compartment. An oil tank is arranged in the core compartment and is axially aligned with the compressor section. A heat exchanger is secured to the oil tank and arranged in the core compartment.

公开(公告)号：US10060350B2

公开(公告)日：2018-08-28

申请号：US14685325

申请日：2015-04-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Harold W. Hipsky ,  Thomas M. Zywiak

IPC: F02C7/04 ,  B64C11/14 ,  F01D25/12 ,  F02C7/14 ,  F02C7/18

CPC classification number: F02C7/04 ,  B64C11/14 ,  F01D25/12 ,  F02C7/14 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/213

Abstract: A nose cone assembly for a gas turbine engine and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone having an aperture communicating air to an interior space of the nose cone and a discharge member communicating the air out of the nose cone.

公开(公告)号：US20180230909A1

公开(公告)日：2018-08-16

申请号：US15947890

申请日：2018-04-09

Applicant: United Technologies Corporation

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

IPC: F02C7/20 ,  F02K1/04 ,  F01D9/04 ,  F01D25/30

CPC classification number: F02C7/20 ,  F01D9/041 ,  F01D25/30 ,  F02K1/04 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/4932

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine case extending along a turbine axis and a CMC turbine exhaust case mounted to the turbine case. The CMC turbine exhaust case includes a CMC core nacelle aft portion, a CMC tail cone connected to the CMC core nacelle aft portion, and a multiple of CMC turbine exhaust case struts extending between the CMC core nacelle aft portion and the CMC tail cone. The CMC core nacelle aft portion, the CMC tail cone and the turbine case are arranged along the turbine axis. The CMC turbine exhaust case is mounted to the turbine case at a flange such that the CMC tail cone is axially spaced apart from the turbine case relative to the turbine axis.