公开(公告)号：US20180080476A1

公开(公告)日：2018-03-22

申请号：US15269342

申请日：2016-09-19

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Gabriel L. Suciu

IPC: F04D29/58 ,  F04D29/54 ,  F04D29/52 ,  F04D29/063

CPC classification number: F04D29/5853 ,  F01D9/06 ,  F02C7/06 ,  F02C7/14 ,  F02C7/18 ,  F02C7/24 ,  F02K3/06 ,  F04D29/063 ,  F04D29/522 ,  F04D29/542 ,  F05D2240/15 ,  F05D2260/231 ,  F05D2260/40311

Abstract: An assembly for use in a gas turbine engine includes a center body support section including inner and outer annular walls, a plurality of struts, and a heat shield. The outer annular wall is disposed radially outward of the inner annular wall and a plurality of struts connect the inner and outer annular walls. The heat shield is disposed radially inward of and connected to the inner annular wall, such that a cavity is formed between the heat shield and the inner annular wall. The cavity is open to an air flow at a forward face of the center body support section. The inner annular wall and heat shield include first and second forward edges, respectively. The first and second forward edges are aligned axially.

公开(公告)号：US09909504B2

公开(公告)日：2018-03-06

申请号：US14440953

申请日：2013-02-20

Applicant: United Technologies Corporation

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

IPC: F02C7/052 ,  F02C7/36 ,  B64D33/02 ,  B64D33/10

CPC classification number: F02C7/36 ,  B64D33/02 ,  B64D33/10 ,  B64D2033/022 ,  F02C7/052 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2250/44 ,  F05D2260/20 ,  Y02T50/675

Abstract: A gas turbine engine comprises an outer nacelle. A nose cone is spaced radially inward of the outer nacelle. The nose cone defines a particle separator for directing an outer air flow and an inner airflow. The inner airflow is directed through a core inlet to a compressor. The engine further comprises a drive gear system for driving at least one propeller. A variable pitch control system may alter a pitch angle of the at least one propeller. Some of the outer air flow is directed to at least one of the drive gear system and the pitch control system.

公开(公告)号：US09897040B2

公开(公告)日：2018-02-20

申请号：US14190171

申请日：2014-02-26

Applicant: United Technologies Corporation

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

IPC: F02K1/60

CPC classification number: F02K1/60 ,  F05D2210/40 ,  F05D2250/314

Abstract: In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a vertical deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.

公开(公告)号：US20180023509A1

公开(公告)日：2018-01-25

申请号：US15218138

申请日：2016-07-25

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F02K1/70 ,  F02K3/062 ,  F02K3/06

CPC classification number: F02K1/70 ,  F02K1/72 ,  F02K3/06 ,  F02K3/062 ,  F05D2220/323 ,  F05D2230/72

Abstract: A gas turbine engine has a core engine and a fan. A pivoting D-door structure includes a pivoting inner D-door portion and an outer D-door portion, which is axially moveable relative to the inner D-door portion between a stowed and thrust reverse position. A fan case surrounds the fan. Cascades are axially moveable along with the outer D-door portion between a stowed and a thrust reverse position. Structure supporting the cascades is mounted on the fan case.

公开(公告)号：US09869183B2

公开(公告)日：2018-01-16

申请号：US14799994

申请日：2015-07-15

Applicant: United Technologies Corporation

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

IPC: F01D5/08 ,  F01D5/28

CPC classification number: F01D5/082 ,  F01D5/084 ,  F01D5/085 ,  F01D5/288 ,  Y02T50/672 ,  Y02T50/676

Abstract: A rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor disk rotatable about an axis and a gas path wall coupled to and radially outward of the rotor disk. The gas path wall bounds a radially inward portion of a gas path. A plurality of rotor spokes are radially intermediate the rotor disk and the gas path wall. The plurality of rotor spokes is circumferentially spaced to define a plurality of cooling channels intermediate the rotor disk and the gas path wall. A thermal barrier coating is disposed on a surface of at least one of the plurality of cooling channels. A method of cooling a rotor assembly is also disclosed.

公开(公告)号：US09850819B2

公开(公告)日：2017-12-26

申请号：US14695504

申请日：2015-04-24

Applicant: United Technologies Corporation

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

IPC: F01D25/12 ,  F02C7/18 ,  F02C7/143 ,  F02C3/13

CPC classification number: F02C7/185 ,  F01D25/12 ,  F02C3/13 ,  F02C7/143 ,  F05D2210/44 ,  F05D2220/3212 ,  F05D2220/3218 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2260/606 ,  Y02T50/676

Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.

公开(公告)号：US20170363098A1

公开(公告)日：2017-12-21

申请号：US15186729

申请日：2016-06-20

Applicant: United Technologies Corporation

Inventor： Stephen H. Taylor ,  Charles E. Lents ,  Gabriel L. Suciu ,  Brian D. Merry ,  Jesse M. Chandler

IPC: F04D27/00 ,  F01D15/12 ,  F01D5/02 ,  F01D17/14 ,  F01D15/08 ,  F04D29/32

CPC classification number: F04D27/009 ,  F01D5/02 ,  F01D15/08 ,  F01D15/12 ,  F01D17/145 ,  F02C6/08 ,  F02C7/32 ,  F04D25/02 ,  F04D27/004 ,  F04D27/023 ,  F04D29/321 ,  F05D2220/32 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine includes a main engine compressor section. A booster compressor changing a pressure of airflow received from the main engine compressor section to a pressure desired for a pneumatic system. The booster compressor operates at airflow conditions greater than a demand by the pneumatic system. A speed change system driving the booster compressor at speeds corresponding to a demand of the pneumatic system. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.

公开(公告)号：US09845159B2

公开(公告)日：2017-12-19

申请号：US14190175

申请日：2014-02-26

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry

IPC: B64D29/06 ,  F02K1/54 ,  F01D13/00 ,  B64D27/20 ,  F02K1/52 ,  F02K1/60 ,  F02K1/64

CPC classification number: B64D29/06 ,  B64D27/20 ,  F01D13/003 ,  F02K1/52 ,  F02K1/54 ,  F02K1/60 ,  F02K1/64 ,  F05D2250/314

Abstract: A system of conjoined gas turbine engines has a first engine with a first propulsor having a first axis and a first engine core having a second axis, and a second engine with a second propulsor having a third axis and a second engine core having a fourth axis. The first axis and third axis are parallel to one another; and the second axis and fourth axis are angled from one another.

公开(公告)号：US20170306850A1

公开(公告)日：2017-10-26

申请号：US15137561

申请日：2016-04-25

Applicant: United Technologies Corporation

Inventor： Joseph Stack ,  Jesse M. Chandler ,  Gabriel L. Suciu ,  Kurt J. Sobanski

IPC: F02C7/24 ,  F02C3/04 ,  F02C7/20

CPC classification number: F02C7/24 ,  F02C3/04 ,  F02C7/20 ,  F02C7/25 ,  F05D2220/32 ,  F05D2260/96

Abstract: An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall. An electronic module assembly of the electromechanical component is connected to the mechanical component and includes a housing, a mounting frame located in the housing and an electronic module secured to the mounting frame. The electronic module is operably connected to the mechanical component via a module cable. A vibration isolator is located in the housing to locate and support the mounting frame therein. The vibration isolator is configured to vibrationally isolate the electronic module from gas turbine engine vibrations. A cover plate is secured to the housing and the first side of the firewall, while the housing extends from the cover plate through a module opening in the firewall to a second side of the firewall having a lower operating temperature than the first side.

公开(公告)号：US20170306840A1

公开(公告)日：2017-10-26

申请号：US15444808

申请日：2017-02-28

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Frederick M. Schwarz ,  William K. Ackermann ,  Daniel Bernard Kupratis

IPC: F02C3/06 ,  F02K3/072

CPC classification number: F02C3/06 ,  F02C3/04 ,  F02C7/36 ,  F02K3/02 ,  F02K3/04 ,  F02K3/06 ,  F02K3/072 ,  F05D2220/3215

Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a performance quantity ratio between about 0.8 and about 1.5.