公开(公告)号：US10024238B2

公开(公告)日：2018-07-17

申请号：US14594663

申请日：2015-01-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Justin J. Phillips ,  James D. Hill ,  William K. Ackermann ,  Chris J. Niggemeier ,  Gabriel L. Suciu ,  Anthony R. Bifulco ,  Julian Partyka

IPC: F02C7/18 ,  F02C6/08 ,  F01D25/08 ,  F01D25/12 ,  F01D9/06 ,  F01D5/18 ,  F01D5/08

Abstract: A cooling system for providing a buffer cooled cooling air to a turbine section of a gas turbine engine is disclosed. The cooling system may comprise a first conduit configured to transmit a cooling air toward the turbine section, a heat exchanger configured to cool a bleed airflow diverted from the first conduit to provide a buffer air, and a bypass conduit configured to direct at least a portion of the buffer air through at least one passageway that bypasses a bearing compartment of the gas turbine engine. The cooling system may further comprise a manifold configured to allow the cooling air exiting the first conduit and the buffer air exiting the bypass conduit to mix and provide the buffer cooled cooling air, and a nozzle assembly configured to deliver the buffer cooled cooling air to the turbine section.

公开(公告)号：US20180195413A1

公开(公告)日：2018-07-12

申请号：US15914519

申请日：2018-03-07

Applicant: United Technologies Corporation

Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Simon Pickford

IPC: F01D25/18 ,  F02C7/32 ,  F02C7/14 ,  F02C7/06 ,  F01D25/12 ,  B64D29/08

CPC classification number: F01D25/18 ,  B64D29/08 ,  B64D33/00 ,  F01D25/12 ,  F01M5/002 ,  F02C7/06 ,  F02C7/14 ,  F02C7/32 ,  F05D2260/2214 ,  F16N19/00 ,  Y02T50/675 ,  Y02T50/676

Abstract: A gas turbine engine includes a fan case radially outwardly of a core compartment. A compressor section is located within an engine core compartment and includes a front mount flange and an aft mount flange. An oil tank is mounted to at least one of the fan case or the front and aft mount flanges. The oil tank has a cooling structure integrated into an outer surface such that the oil tank is subjected to cooling air flow from a plurality of air sources.

公开(公告)号：US10001063B2

公开(公告)日：2018-06-19

申请号：US14440698

申请日：2013-03-14

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C3/04 ,  F02C7/20 ,  B64D27/20 ,  B64D33/02

CPC classification number: F02C7/20 ,  B64D27/20 ,  B64D33/02 ,  B64D2033/0286 ,  F05D2250/314

Abstract: A propulsion system for an aircraft includes first and second turbine engines mounted within a fuselage of the aircraft. The first turbine engine includes a first engine core that drives a first propulsor disposed about a first propulsor axis. The second turbine engine includes a second engine core and a second propulsor disposed about a second propulsor axis parallel to the first propulsor axis. The first engine core and the second engine core are mounted at an angle relative to corresponding ones of the first and second propulsor axes.

公开(公告)号：US09988986B2

公开(公告)日：2018-06-05

申请号：US14600445

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill ,  William Ackermann

IPC: F02C7/12

CPC classification number: F02C7/12 ,  F05D2260/213

Abstract: The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit.

公开(公告)号：US09970323B2

公开(公告)日：2018-05-15

申请号：US14427664

申请日：2013-03-14

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C3/04 ,  F01D25/24 ,  F02C6/08 ,  F02C3/10 ,  F02C7/36

CPC classification number: F01D25/24 ,  F01D25/243 ,  F02C3/10 ,  F02C6/08 ,  F02C7/36 ,  F05D2250/30 ,  F05D2260/40311

Abstract: A gas turbine engine has a compressor section, a compressor case substantially surrounding the compressor section, and a diffuser case attached at an attachment interface to the compressor case. The attachment interface is between a forward and an aft end of the compressor. A geared turbofan is also disclosed.

公开(公告)号：US20180128169A9

公开(公告)日：2018-05-10

申请号：US14120450

申请日：2014-06-27

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C6/08 ,  F02C9/18 ,  F02C7/32

CPC classification number: F02C6/08 ,  B64D13/04 ,  B64D2013/0644 ,  F02C7/32 ,  F02C9/18 ,  F05D2220/323

Abstract: A gas turbine engine assembly for an aircraft includes a fan section delivering air into a main compressor section. The main compressor section includes a first compressor section and a second compressor section operating at a higher pressure than the first compressor section. The main compressor section compresses air and delivers air into a combustion section where the air is mixed with fuel and ignited to generate products of combustion that are passed over a turbine section to drive the fan section and main compressor sections. An environmental control system includes a low pressure tap at a location on the first compressor section of the main compressor section. The low pressure tap communicates airflow to a first passage leading to a downstream outlet. A compressor is driven by an electric motor. A combined outlet intermixes airflow from the first passage and from the compressor driven by the electric motor and passes the airflow downstream to be delivered to an aircraft use. An environmental control system is also disclosed.

公开(公告)号：US09964036B2

公开(公告)日：2018-05-08

申请号：US14120450

申请日：2014-06-27

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: B64D13/04 ,  F02C6/08 ,  F02C9/18 ,  F02C7/32 ,  B64D13/06

CPC classification number: F02C6/08 ,  B64D13/04 ,  B64D2013/0644 ,  F02C7/32 ,  F02C9/18 ,  F05D2220/323

Abstract: An environmental control system includes a low pressure tap at a location on a first compressor section of a main compressor section. The low pressure tap communicates airflow to a first passage leading to a downstream outlet. A compressor is driven by an electric motor. A combined outlet intermixes airflow from the first passage and from the compressor driven by the electric motor and passes the airflow downstream to be delivered to an aircraft use.

公开(公告)号：US09963977B2

公开(公告)日：2018-05-08

申请号：US14868903

申请日：2015-09-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  James D. Hill ,  Gopal Das

IPC: F01D5/28 ,  F01D5/02 ,  F01D5/14

CPC classification number: F01D5/28 ,  F01D5/02 ,  F01D5/147 ,  F05D2230/23 ,  F05D2230/60 ,  F05D2240/24 ,  F05D2300/174 ,  F05D2300/5023 ,  Y02T50/671

Abstract: Components include a low pressure turbine having a plurality of rotor assemblies including a first gamma TiAl intermetallic blade having a maximum operating temperature over 1180° F. (638° C.). At least two of the rotor assemblies include gamma TiAl intermetallic alloy blades. In an embodiment, a method of making a turbine having a plurality of rotor assemblies includes attaching a first gamma TiAl intermetallic alloy blade to an upstream stage of the plurality of rotor assemblies.

公开(公告)号：US09957895B2

公开(公告)日：2018-05-01

申请号：US14771061

申请日：2014-02-28

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/18 ,  F02C7/06 ,  F02C7/14 ,  F01D9/04 ,  F01D9/06 ,  F01D5/02 ,  F02C3/04 ,  F02C7/04 ,  F01D25/24 ,  F04D29/54 ,  F01D25/12 ,  F01D17/10 ,  F02C6/08

CPC classification number: F02C7/18 ,  F01D5/02 ,  F01D9/041 ,  F01D9/065 ,  F01D17/105 ,  F01D25/12 ,  F01D25/24 ,  F02C3/04 ,  F02C6/08 ,  F02C7/04 ,  F02C7/06 ,  F02C7/14 ,  F04D29/541 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2260/20 ,  F05D2260/213 ,  Y02T50/676

Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section with a multiple of pre-swirlers, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said multiple of pre-swirlers.

公开(公告)号：US20180094532A1

公开(公告)日：2018-04-05

申请号：US15816512

申请日：2017-11-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Jason Husband ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F01D15/12 ,  F02K3/06 ,  F04D29/053 ,  F04D25/04 ,  F04D19/00 ,  F01D5/06

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D9/041 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/002 ,  F04D25/045 ,  F04D29/053 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2300/501 ,  Y02T50/671

Abstract: A gas turbine engine includes a fan shaft that has fan blades. A fan shaft is drivingly connected to the fan. A fan shaft support supports the fan shaft and defines a fan shaft support lateral stiffness. A gear system is connected to the fan shaft and driven through an input. A gear system flex mount arrangement accommodates misalignment of the fan shaft and the input during operation and includes a flexible support that defines a flexible support lateral stiffness that is less than 11% of the shaft support lateral stiffness.