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：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.

公开(公告)号：US20180058328A1

公开(公告)日：2018-03-01

申请号：US15244025

申请日：2016-08-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Paul W. Duesler

IPC: F02C7/141 ,  F02C7/18 ,  F02C9/18

CPC classification number: F02C7/141 ,  F02C7/18 ,  F02C7/185 ,  F02C9/18 ,  F05C2201/90 ,  F05D2260/213 ,  F05D2300/1723 ,  F05D2300/176 ,  Y02T50/676

Abstract: A gas turbine engine has a compressor section including a lower pressure compressor and a higher pressure compressor, and a turbine section. A core engine housing surrounds the compressor section and the turbine section. An outer intermediate housing wall defines an internal chamber between the core housing and the outer intermediate housing. A fan rotor and a fan casing surround the fan rotor to define a bypass duct between the fan case and the outer intermediate housing. A heat exchanger is mounted in the internal chamber and receives high pressure air for cooling the high pressure air and delivering the high pressure air into the core engine housing to be utilized as cooling air for a component. Air from the lower pressure compressor is utilized to cool the higher pressure air in the heat exchanger.

公开(公告)号：US20180003112A1

公开(公告)日：2018-01-04

申请号：US15420221

申请日：2017-01-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

IPC: F02C7/32 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F02K3/072 ,  F02C3/107

Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

公开(公告)号：US20170363012A1

公开(公告)日：2017-12-21

申请号：US15186839

申请日：2016-06-20

Applicant: United Technologies Corporation

Inventor： Jesse W. Clauson ,  Frederick M. Schwarz

IPC: F02C9/00 ,  F01D25/36 ,  F02C3/04

Abstract: A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes a full authority digital engine control (FADEC) that controls operation of the gas turbine engine in a full-power mode and controls operation of the core turning motor to drive rotation of the engine core using a reduced power draw when the FADEC is partially depowered in a low-power bowed rotor prevention mode.

公开(公告)号：US20170307311A1

公开(公告)日：2017-10-26

申请号：US15138491

申请日：2016-04-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Paul W. Duesler

IPC: F28F21/08 ,  F28F1/28 ,  F02C9/18 ,  F02C3/04 ,  F28F1/40 ,  F02C7/18 ,  F28D1/047

CPC classification number: F28F21/087 ,  F01D9/065 ,  F02C7/185 ,  F02K3/02 ,  F05D2260/213 ,  F05D2300/175 ,  F05D2300/182 ,  F28D1/0475 ,  F28D7/12 ,  F28F1/28 ,  F28F1/40 ,  Y02T50/676

Abstract: A heat exchanger system for use in a gas turbine engine has a plurality of circumferentially spaced heat exchangers. The spaced heat exchangers are formed of a nickel alloy material including more than 50-percent by volume gamma-prime intermetallic phase material. A gas turbine engine is also disclosed.

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.

公开(公告)号：US20170298833A1

公开(公告)日：2017-10-19

申请号：US15488580

申请日：2017-04-17

Applicant: United Technologies Corporation

Inventor： David P. Houston ,  Daniel Bernard Kupratis ,  Frederick M. Schwarz

IPC: F02C7/36 ,  F01D5/02 ,  F02K3/072 ,  F01D25/16 ,  F02C7/06

CPC classification number: F02K3/06 ,  F01D5/02 ,  F01D5/06 ,  F01D9/02 ,  F01D9/041 ,  F01D25/164 ,  F02C3/04 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02C9/18 ,  F02K1/78 ,  F02K3/072 ,  F04D27/009 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2240/40 ,  F05D2250/30 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/671 ,  Y02T50/673

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 ratio between about 0.5 and about 1.5.