公开(公告)号：US10414509B2

公开(公告)日：2019-09-17

申请号：US15439988

申请日：2017-02-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64D27/00 ,  B64D27/26 ,  B64D27/20 ,  B64D35/04

Abstract: A propulsor and mount arrangement comprises a propulsor rotor and a fan casing surrounding the propulsor rotor. The fan casing receives two side mounts and a thrust link pivotally attached to the fan casing at a location that will be within 10° of a vertically lowermost location when the propulsor is mounted on an aircraft, and the side mounts being at circumferentially opposed positions, and within a lower 270° when the propulsor is mounted on an aircraft. At least a portion of both the side mounts, and a pivot point connect the thrust link to the fan casing in a common plane defined perpendicular to a rotational axis of the propulsor rotor. An aircraft is also disclosed.

公开(公告)号：US10400629B2

公开(公告)日：2019-09-03

申请号：US14012576

申请日：2013-08-28

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Todd A. Davis ,  Gregory E. Reinhardt ,  Enzo DiBenedetto

IPC: F02C7/06 ,  F01D25/16 ,  F02C7/36 ,  F02K3/04

Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.

公开(公告)号：US10378374B2

公开(公告)日：2019-08-13

申请号：US14672561

申请日：2015-03-30

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Nathan Snape

IPC: F01D11/14 ,  F01D25/24 ,  F01D25/14 ,  F01D17/00 ,  F02C5/12 ,  F01D11/24 ,  F02C7/25

Abstract: A gas turbine engine includes a fluid intake. A turbine section includes a turbine case. A firewall is located upstream of the turbine section. A conduit is configured to direct a fluid from the fluid intake to the turbine case. A valve is located on a first side of the firewall opposite from the turbine section and is configured to regulate a flow of the fluid through the conduit.

公开(公告)号：US10371061B2

公开(公告)日：2019-08-06

申请号：US15292405

申请日：2016-10-13

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph Brent Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C3/107 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F01D5/06 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D19/02 ,  F01D11/12

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

公开(公告)号：US10371056B2

公开(公告)日：2019-08-06

申请号：US14964984

申请日：2015-12-10

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/18 ,  F01D25/08 ,  F01D5/02 ,  F02C7/36 ,  F02K3/06 ,  F01D5/08 ,  F02C6/08 ,  F02C7/12

Abstract: A gas turbine engine comprises a compressor section and a turbine section, with the turbine section having a first stage blade row and a downstream blade row. A higher pressure tap is tapped from a higher pressure first location in the compressor. A lower pressure tap is tapped from a lower pressure location in the compressor which is at a lower pressure than the first location. The higher pressure tap passes through a heat exchanger, and then is delivered to cool the first stage blade row in the turbine section. The lower pressure tap is delivered to at least partially cool the downstream blade row.

公开(公告)号：US10358981B2

公开(公告)日：2019-07-23

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 ,  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：US10352274B2

公开(公告)日：2019-07-16

申请号：US15240104

申请日：2016-08-18

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02K3/062 ,  B64D27/14 ,  B64C11/46 ,  F02C7/36 ,  F02C3/10

Abstract: An aircraft engine includes a gas powered turbine core. A first fan is connected to the turbine core via a shaft. The fan is positioned aft of the turbine. A second fan is connected to the first fan via a geared connection.

公开(公告)号：US20190154059A1

公开(公告)日：2019-05-23

申请号：US16251133

申请日：2019-01-18

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Brian D. Merry

IPC: F04D29/58 ,  F01D25/12 ,  F02C6/08 ,  F02C7/143 ,  F02C3/13 ,  F02C7/18 ,  F02C9/18

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

公开(公告)号：US20190153887A1

公开(公告)日：2019-05-23

申请号：US16173051

申请日：2018-10-29

Applicant: United Technologies Corporation

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

IPC: F01D15/12 ,  F02C7/36 ,  F16H57/04 ,  F01D25/18 ,  F16H1/28 ,  F02K3/06

CPC classification number: F01D15/12 ,  F01D25/18 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/50 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H1/28 ,  F16H57/0479 ,  F16H57/0486

Abstract: A turbofan engine assembly includes a nacelle and a turbofan engine. The turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades. A turbine rotor drives the fan rotor. An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and four intermediate gears that engage the sun gear and the ring gear. A gear ratio of the gear reduction is greater than 3.06. The fan drive turbine drives the sun gear to, in turn, drive the fan rotor.

公开(公告)号：US10287024B2

公开(公告)日：2019-05-14

申请号：US15228359

申请日：2016-08-04

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64D27/14 ,  B64D33/04 ,  F01D5/02 ,  F01D9/02 ,  F02K3/062 ,  F04D29/32 ,  F02C3/10 ,  B64D33/02

Abstract: An aircraft engine includes a gas generator, a turbine fluidly connected to the gas generator, and a fan connected to the turbine via a shaft. The fan is positioned aft of the turbine, and the shaft is at least partially disposed in a fan inlet flowpath.