公开(公告)号：US10006370B2

公开(公告)日：2018-06-26

申请号：US14745539

申请日：2015-06-22

Applicant: United Technologies Corporation

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

IPC: F01D25/08 ,  F02C7/18

CPC classification number: F02C7/18 ,  F05D2260/213 ,  Y02T50/676

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, 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 air downstream of the heat exchanger, and delivers air into the high pressure turbine. A core housing has an outer peripheral surface and a fan housing defining an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is received within the at least one bifurcation duct.

公开(公告)号：US10006364B2

公开(公告)日：2018-06-26

申请号：US14813284

申请日：2015-07-30

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D5/06 ,  F02C7/12 ,  F01D5/08 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F01D11/00 ,  F01D25/12 ,  F04D29/32 ,  F04D29/16 ,  F04D29/54 ,  F04D29/58

CPC classification number: F02C7/12 ,  F01D5/066 ,  F01D5/084 ,  F01D5/087 ,  F01D11/001 ,  F01D25/12 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D29/164 ,  F04D29/321 ,  F04D29/545 ,  F04D29/584 ,  F05D2220/32 ,  F05D2260/221 ,  Y02T50/676

Abstract: A rotor for a gas turbine engine includes a cold shell, a hot shell, and a spoke. The spoke is connected to and extends radially outward from the cold shell. The hot shell is connected to the cold shell by the spoke and includes an axially extending outboard segment and an axially extending inboard segment. The outboard segment is connected to the inboard segment and the inboard segment is disposed radially inboard of the outboard segment for sealably engaging a stator blade shroud.

公开(公告)号：US10006302B2

公开(公告)日：2018-06-26

申请号：US14788345

申请日：2015-06-30

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Simon Pickford ,  William K. Ackermann ,  Nathan Snape

IPC: F01D9/06 ,  F01D1/02 ,  F01D25/12 ,  F01D5/02 ,  F01D9/02 ,  F02C7/18 ,  F02C7/32 ,  F02C7/047 ,  F02C7/04

CPC classification number: F01D9/065 ,  F01D1/02 ,  F01D5/02 ,  F01D9/02 ,  F01D25/12 ,  F02C7/04 ,  F02C7/047 ,  F02C7/18 ,  F02C7/32 ,  F05D2220/30 ,  F05D2260/20 ,  F05D2260/213 ,  Y02T50/675

Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump at least partially within an interior of the nose cone. The pump is selectively rotated by a motor to communicate air to the interior.

公开(公告)号：US20180171815A1

公开(公告)日：2018-06-21

申请号：US15827132

申请日：2017-11-30

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian Merry ,  William G. Sheridan ,  Michael E. McCune

IPC: F01D15/12 ,  F01D15/08 ,  F01D15/10 ,  F16H1/22 ,  F16H15/04 ,  F16H37/02

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D15/08 ,  F01D15/10 ,  F01D25/16 ,  F01D25/18 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/402 ,  F05D2260/4031 ,  F05D2270/024 ,  F16H1/222 ,  F16H15/04 ,  F16H37/021

Abstract: A gas turbine engine assembly according to an example of the present disclosure includes, among other things, 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, an accessory drive gearbox a first towershaft interconnecting the accessory drive gearbox and the first or second turbine shaft, and a multispeed transmission interconnecting the accessory drive gearbox and at least one accessory component.

公开(公告)号：US10001059B2

公开(公告)日：2018-06-19

申请号：US14753474

申请日：2015-06-29

Applicant: United Technologies Corporation

Inventor： Hung Duong ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02C7/36 ,  F16H1/20 ,  F02C7/00 ,  F02C7/32

CPC classification number: F02C7/00 ,  F02C7/32 ,  F02C7/36 ,  F05D2230/70 ,  F05D2250/312 ,  F16H1/20 ,  Y10T29/49464

Abstract: An accessory system for a gas turbine engine includes an accessory gearbox which defines an accessory gearbox axis and includes first and second sides. A first geartrain includes one or more shafts rotatable about axes perpendicular to the first side of the accessory gearbox and a second geartrain includes one or more shafts rotatable about axes perpendicular to the second side of the accessory gearbox. A driven gear set defines an input axis and drives first geartrain and the second geartrain about corresponding first and second drive axes parallel to the input axis.

公开(公告)号：US20180163627A1

公开(公告)日：2018-06-14

申请号：US15809244

申请日：2017-11-10

Applicant: United Technologies Corporation

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

IPC: F02C7/18 ,  F02C3/04 ,  F02C6/08 ,  F02K3/04 ,  F02C9/18

Abstract: An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.

公开(公告)号：US20180156109A1

公开(公告)日：2018-06-07

申请号：US15371589

申请日：2016-12-07

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C6/08 ,  F02K3/06 ,  F02C7/36 ,  F02C3/20 ,  B64D33/02

CPC classification number: F02C6/08 ,  B64C1/16 ,  B64C21/00 ,  B64C2230/04 ,  B64D27/20 ,  B64D33/02 ,  B64D2033/0226 ,  F02C3/10 ,  F02C3/20 ,  F02C7/36 ,  F02K3/06 ,  F02K3/062 ,  F05D2220/323 ,  F05D2220/50 ,  F05D2220/76

Abstract: A boundary layer ingestion engine includes a gas generator and a turbine fluidly connected to the gas generator. A fan is mechanically linked to the turbine via a shaft such that rotation of the turbine is translated to the fan. A boundary layer ingestion inlet is aligned with an expected boundary layer, such that the boundary layer ingestion inlet is configured to ingest fluid from a boundary layer during operation of the boundary layer ingestion engine.

公开(公告)号：US20180155045A1

公开(公告)日：2018-06-07

申请号：US15874335

申请日：2018-01-18

Applicant: United Technologies Corporation

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

IPC: B64D35/08 ,  B64C11/00 ,  B64C21/06 ,  B64C39/00 ,  B64D35/02 ,  B64C1/06

CPC classification number: B64D35/08 ,  B64C1/068 ,  B64C5/02 ,  B64C11/006 ,  B64C21/06 ,  B64C23/02 ,  B64C39/005 ,  B64C2230/04 ,  B64D27/02 ,  B64D35/02 ,  B64D41/00 ,  F04D17/04

Abstract: A cross flow fan to be incorporated into an aircraft fuselage comprises an ingestion fan rotor to be positioned in a tail section of an aircraft fuselage to reduce boundary layer air from a top surface of the fuselage and to drive the air away from the top surface, and a drive arrangement for the ingestion fan rotor. An aircraft is also disclosed.

公开(公告)号：US09989011B2

公开(公告)日：2018-06-05

申请号：US14639164

申请日：2015-03-05

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Daniel Bernard Kupratis

IPC: F02K3/06 ,  F02K3/04 ,  F02C3/06 ,  F02K3/02 ,  F01D13/00 ,  F02C7/36 ,  F02K1/52

CPC classification number: F02K3/04 ,  F01D13/003 ,  F01D13/006 ,  F02C3/06 ,  F02C7/36 ,  F02K1/52 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/323 ,  F05D2250/314 ,  F05D2260/4031

Abstract: A bypass housing receives a fan and defines a front end. An airflow path delivers air into an inlet duct over a limited circumferential extent of the bypass housing. An airflow path passes across a low pressure compressor rotor. An airflow path passes through a core engine, which includes a high pressure compressor rotor, a combustor, and a high pressure turbine rotor. Products of combustion downstream of the high pressure turbine rotor pass into an intermediate duct and then across a low pressure turbine rotor. The low pressure turbine rotor is positioned closer to the front end of the engine than is the high pressure turbine rotor. The low pressure turbine rotor is positioned axially intermediate the low pressure compressor rotor and the fan. The low pressure turbine rotor drives both the fan and the low pressure turbine rotor. An aircraft is also disclosed.

公开(公告)号：US09976485B2

公开(公告)日：2018-05-22

申请号：US14695142

申请日：2015-04-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Ioannis Alvanos

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

CPC classification number: F02C7/185 ,  F01D5/081 ,  F01D25/125 ,  F02C6/08 ,  F02C7/06 ,  F05D2220/32 ,  F05D2260/232

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger configured to exchange heat with a bleed airflow to provide a conditioned airflow. A bearing compartment is in fluid communication with the heat exchanger, and a first passageway communicates the conditioned airflow to the bearing compartment. The conditioned airflow is communicated radially between a bearing housing of the bearing compartment and a diffuser case and a nozzle assembly in fluid communication with the bearing compartment. A second passageway communicates the conditioned airflow from the bearing compartment and then through a plurality of openings of the nozzle assembly.