公开(公告)号：US20130192200A1

公开(公告)日：2013-08-01

申请号：US13645606

申请日：2012-10-05

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

IPC: F02K3/075

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D9/02 ,  F01D9/065 ,  F02C3/04 ,  F02C3/107 ,  F02C3/36 ,  F02C7/06 ,  F02C9/18 ,  F02K1/78 ,  F02K3/04 ,  F02K3/06 ,  F02K3/072 ,  F04D27/009 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  Y02T50/671

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：US11635025B2

公开(公告)日：2023-04-25

申请号：US14432289

申请日：2013-09-27

Applicant: United Technologies Corporation

Inventor： David Bomzer ,  Frederick M. Schwarz

IPC: F01D5/02 ,  F02C7/20 ,  F02C3/107 ,  B64D27/26 ,  F02C7/36 ,  B65D27/26

Abstract: A gas turbine engine includes a plurality of fan blades rotatable about an axis, wherein each of the plurality of fan blades includes a leading edge. The gas turbine engine also includes turbine section includes an aft most turbine blade having a trailing edge and a geared architecture driven by the turbine section for rotating the plurality of fan blades about the axis. A center of gravity of the gas turbine engine is located a first axial distance from the trailing edge of the aft most turbine blade that is between about 35% and about 75% of a total length between the leading edge of the plurality of fan blades and the trailing edge of the aft most turbine blade.

公开(公告)号：US11421598B2

公开(公告)日：2022-08-23

申请号：US16781424

申请日：2020-02-04

Applicant: United Technologies Corporation

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F28D1/053 ,  F28F13/06 ,  F28D1/04 ,  F28F13/08 ,  F02K3/115 ,  F02C7/14 ,  F28D21/00 ,  F28D1/02 ,  F02C3/04 ,  F02C7/36 ,  F02C9/18

Abstract: A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.

公开(公告)号：US11305879B2

公开(公告)日：2022-04-19

申请号：US16360277

申请日：2019-03-21

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael Winter

IPC: F17C7/02 ,  B64D13/08 ,  F02C7/141 ,  F02C7/16 ,  F02C9/18 ,  F25B9/14 ,  F25J3/04 ,  B01D45/08 ,  B01D53/00 ,  B03C1/28 ,  B64D27/12 ,  B64D33/08 ,  F01D15/00 ,  F01D25/12 ,  F02C6/08 ,  F02C7/143 ,  F02C7/18 ,  F02K3/06 ,  B64D13/06 ,  F17C7/04 ,  B64D37/32

Abstract: A propulsion system includes an electric fan propulsion motor with a plurality of propulsion motor windings. The propulsion system also includes a means for controlling a flow rate of a working fluid through a cryogenic working fluid flow control assembly to the propulsion motor windings. The propulsion system further includes a controller operable to control supplying a pre-cooling flow of the working fluid from a cryogenic liquid reservoir through the cryogenic working fluid flow control assembly to the propulsion motor windings.

公开(公告)号：US11105221B2

公开(公告)日：2021-08-31

申请号：US16362028

申请日：2019-03-22

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Simon Pickford

IPC: F01D25/12 ,  F02K3/06 ,  F02K3/115 ,  F02C7/14 ,  F01D15/12 ,  F01D17/10 ,  F01D5/02

Abstract: A method of sizing a heat exchanger for a geared architecture gas turbine engine includes sizing a minimum frontal area of at least one heat exchanger located in communication with a fan bypass airflow such that a ratio of waste heat area to horsepower generation characteristic area is between 1.6 to 8.75.

公开(公告)号：US11073106B2

公开(公告)日：2021-07-27

申请号：US15881240

申请日：2018-01-26

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F02K3/06 ,  F02C3/107 ,  F02C7/36 ,  F02C7/20 ,  F01D15/12 ,  F01D5/06 ,  F04D19/00 ,  F04D25/04 ,  F04D29/053 ,  F04D29/32 ,  F01D9/04

Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with some flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is relatively high.

公开(公告)号：US11053816B2

公开(公告)日：2021-07-06

申请号：US15007263

申请日：2016-01-27

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C3/06 ,  F01D25/24 ,  F02K3/06 ,  F16H1/28 ,  F02C3/107 ,  F01D5/02 ,  F01D5/12 ,  F01D17/10 ,  F04D29/32 ,  F02C7/36

Abstract: A front section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan hub. The fan hub includes a hub diameter supporting a plurality of fan blades including a tip diameter. A transitional entrance passage is configured to communicate flow between the fan section and a compressor section. The transitional entrance passage includes an inlet disposed at an inlet diameter and an outlet to the compressor section disposed at an outlet diameter. A method of designing a gas turbine engine is also disclosed.

公开(公告)号：US10982595B2

公开(公告)日：2021-04-20

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

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：US10941708B2

公开(公告)日：2021-03-09

申请号：US15452632

申请日：2017-03-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Steven D. Sandahl

IPC: F02C7/045 ,  F01D25/06 ,  F01D5/26 ,  F02K3/06 ,  B65D33/02 ,  B64D33/02

Abstract: Disclosed is a gas turbine engine including a fan, a nacelle including a flutter damper forward of the fan, the flutter damper including an acoustic liner having a perforated radial inner face sheet and a radial outer back sheet, the acoustic liner configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber secured to the radial outer back sheet, the chamber in fluid communication with the acoustic liner, and the chamber configured for peak acoustical energy absorption at a frequency range associated with fan flutter modes, and the engine includes (i) the nacelle and a core cowl forming a convergent-divergent fan exit nozzle; (ii) a variable area fan nozzle capable of being in an opened and closed, the opened position having a larger fan exit area than the closed position; and/or (iii) the fan being shrouded.

公开(公告)号：US10801355B2

公开(公告)日：2020-10-13

申请号：US16173051

申请日：2018-10-29

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan ,  Michael E. McCune ,  Gabriel L. Suciu

IPC: F01D15/12 ,  F02C7/36 ,  F01D25/18 ,  F02K3/06 ,  F16H1/28 ,  F16H57/04

Abstract: A turbofan engine assembly includes a nacelle and a turbofan engine. The turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades. A turbine rotor drives the fan rotor. An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and four intermediate gears that engage the sun gear and the ring gear. A gear ratio of the gear reduction is greater than 3.06. The fan drive turbine drives the sun gear to, in turn, drive the fan rotor.