公开(公告)号：US20180230944A1

公开(公告)日：2018-08-16

申请号：US15943100

申请日：2018-04-02

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian Merry ,  Christopher M. Dye

IPC: F02K3/06 ,  F02C7/36

CPC classification number: F02K3/06 ,  F02C7/36

Abstract: A turbine engine is disclosed that includes a fan case surrounding a fan rotatable about an axis. A core is supported relative to the fan case by support structure arranged downstream from the fan. The core includes a core housing having an inlet case arranged to receive airflow from the fan. A compressor case is arranged axially adjacent to the inlet case and surrounds a compressor stage having a rotor blade with a blade trailing edge. The support structure includes a support structure leading edge facing the fan and a support structure trailing edge on a side opposite the support structure leading edge. The support structure trailing edge is arranged axially forward of the blade trailing edge. In one example, a forward attachment extends from the support structure to the inlet case.

公开(公告)号：US20180209343A1

公开(公告)日：2018-07-26

申请号：US15410971

申请日：2017-01-20

Applicant: United Technologies Corporation

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

IPC: F02C7/18 ,  F02K3/06 ,  F02C3/04

CPC classification number: F02C7/185 ,  F02C3/04 ,  F02K3/06 ,  F05D2260/213 ,  Y02T50/676

Abstract: An intercooled cooling system for a gas turbine engine includes a heat exchanger in fluid communication with a cooling airflow source directed through the heat exchanger and an auxiliary compressor fluidly coupled to the heat exchanger via a discharge duct to compress the cooling airflow exiting the heat exchanger. A compressor discharge pathway directs a first portion of the cooling airflow from the auxiliary compressor to a first cooling location of the gas turbine engine, and a bypass pathway is fluidly coupled to the discharge duct between the heat exchanger and the auxiliary compressor to direct a second portion of the cooling airflow to a second cooling location of the gas turbine without passing through the auxiliary compressor.

公开(公告)号：US20180202366A1

公开(公告)日：2018-07-19

申请号：US15409889

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 ,  F02C7/06 ,  F02C7/36

CPC classification number: F02C7/32 ,  F02C7/06 ,  F02C7/36 ,  F05D2220/76 ,  F05D2240/50 ,  F05D2260/4031

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, the accessory drive gearbox including a first set of gears and a second set of gears, the first towershaft extending into a housing and coupled to the first set of gears, the second towershaft extending into the housing and coupled to the second set of gears, an electric machine, and a transmission coupling the electric machine to the first set of gears, the transmission transitionable between a first mode where the electric machine is driven at a first speed relative to the first towershaft, and a second mode where the electric machine is driven at a different, second speed relative to the first towershaft.

公开(公告)号：US20180202310A1

公开(公告)日：2018-07-19

申请号：US15410049

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: F01D15/12 ,  F02C7/268 ,  F01D5/06 ,  F01D15/10 ,  F01D25/20 ,  F16H3/30

Abstract: An exemplary gas turbine engine assembly includes a transmission coupling a starter generator assembly to a first set of gears. The transmission is transitionable between a first mode where the starter generator assembly is driven at a first speed relative to the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft.

公开(公告)号：US20180080373A1

公开(公告)日：2018-03-22

申请号：US15268713

申请日：2016-09-19

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Tania Bhatia Kashyap ,  Mark F. Zelesky ,  Arthur W. Utay ,  Gabriel L. Suciu ,  Thomas N. Slavens ,  Kevin L. Rugg ,  Brian Merry

IPC: F02C3/107 ,  F02C3/14

CPC classification number: F02C3/107 ,  F02C3/145 ,  F02C7/04 ,  F05D2240/40 ,  F05D2250/30

Abstract: A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.

公开(公告)号：US10995673B2

公开(公告)日：2021-05-04

申请号：US15410113

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 ,  F02C3/06 ,  F02C7/18 ,  F02C7/36 ,  F02C7/268 ,  F01D15/10 ,  F01D25/12 ,  F16H1/22 ,  H02K7/116 ,  H02K7/18 ,  F01D15/12 ,  F02C7/275

Abstract: An exemplary gas turbine engine assembly includes a first spool having a first turbine operatively mounted to a first turbine shaft, and a second spool having a second turbine operatively mounted to a second turbine shaft. The first and second turbines are mounted for rotation about a common rotational axis within an engine static structure. The first and second turbine shafts are coaxial with one another. First and second towershafts are respectively coupled to the first and second turbine shafts. An accessory drive gearbox has a set of gears. A compressor is driven by the first towershaft. The engine assembly further includes a starter generator assembly, and a transmission coupling the starter generator assembly to the first set of gears. The transmission is transitionable between a first mode where the starter generator assembly is driven at a first speed relative to the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft.

公开(公告)号：US20200173297A1

公开(公告)日：2020-06-04

申请号：US16207669

申请日：2018-12-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brian Merry ,  Paul W. Duesler

IPC: F01D11/08

Abstract: A gas turbine engine may include a rotor overspeed protection (ROP) assembly. The ROP assembly may include an annular blade outer air seal (BOAS) assembly including a ROP segment. The ROP assembly may include a stator vane coupled with the BOAS assembly/. The stator vane may include a stator flange disposed about a forward edge portion of the stator vane. The ROP segment may include a ROP flange extending in an axially aft direction from a main body of the ROP segment toward the stator vane, wherein the ROP flange is disposed radially inward of the stator flange.

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：US20180320542A1

公开(公告)日：2018-11-08

申请号：US15589009

申请日：2017-05-08

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D11/24

Abstract: A clearance control system for a gas turbine engine comprises at least one case support associated with an engine case defining an engine center axis. A clearance control ring is positioned adjacent the at least one case support to form an internal cavity between the engine case and the clearance control ring. The clearance control ring includes a first mount feature. An outer air seal has a second mount feature cooperating with the first mount feature such that the clearance control ring can move independently of the engine case in response to changes in temperature. An injection source inject flow into the internal cavity to control a temperature of the clearance control ring to allow the outer air seal to move in a desired direction to maintain a desired clearance between the outer air seal and an engine component. A gas turbine engine and a method of controlling tip clearance in a gas turbine engine are also disclosed.

公开(公告)号：US10060354B2

公开(公告)日：2018-08-28

申请号：US15445521

申请日：2017-02-28

Applicant: United Technologies Corporation

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

IPC: B64D27/10 ,  F02C7/20 ,  B64D27/26

CPC classification number: F02C7/20 ,  B64D27/10 ,  B64D27/26 ,  B64D2027/262 ,  B64D2027/266 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2240/90 ,  Y02T50/44 ,  Y10T29/49947

Abstract: A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.