公开(公告)号：US09752511B2

公开(公告)日：2017-09-05

申请号：US15484441

申请日：2017-04-11

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D25/00 ,  F02C7/36 ,  F04D25/04 ,  F04D29/32 ,  F01D5/06 ,  F01D9/04 ,  F01D15/12 ,  F02K3/06

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 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：US09739205B2

公开(公告)日：2017-08-22

申请号：US14573812

申请日：2014-12-17

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F02C3/107

CPC classification number: F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a combustor section located axially upstream of the drive turbine, and a speed change mechanism located axially downstream of the combustor section and axially upstream of the drive turbine. An output of the speed change mechanism connects to the fan.

公开(公告)号：US20170234233A1

公开(公告)日：2017-08-17

申请号：US15042724

申请日：2016-02-12

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Amy R. Grace

IPC: F02C7/27 ,  G05B15/02 ,  F02C7/06 ,  F01D25/24 ,  F02K3/04 ,  F02C3/107

CPC classification number: F02C7/27 ,  F01D19/02 ,  F01D25/24 ,  F01D25/34 ,  F02C3/107 ,  F02C7/06 ,  F02C7/268 ,  F02K3/04 ,  F05D2220/323 ,  F05D2260/85 ,  F05D2270/021 ,  F05D2270/114 ,  F05D2270/304 ,  F05D2270/334 ,  G05B15/02

Abstract: A bowed rotor start mitigation system for a gas turbine engine of an aircraft is provided. The bowed rotor start mitigation system includes a motoring system and a controller coupled to the motoring system and an aircraft communication bus. The controller is configured to determine at least one inferred engine operating thermal parameter from at least one aircraft-based parameter received on the aircraft communication bus. The motoring system is controlled to drive rotation of a starting spool of the gas turbine engine below an engine idle speed based on determining that the at least one inferred engine operating thermal parameter is within a preselected threshold.

公开(公告)号：US20170204787A1

公开(公告)日：2017-07-20

申请号：US15000618

申请日：2016-01-19

Applicant: United Technologies Corporation

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C9/18 ,  F02C7/14 ,  F01D25/24 ,  F02C7/36 ,  F02C3/04 ,  F02C7/18

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：US20170175874A1

公开(公告)日：2017-06-22

申请号：US14976166

申请日：2015-12-21

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael E. McCune

IPC: F16H57/04 ,  F02C7/36

CPC classification number: F16H57/0435 ,  F01D21/00 ,  F01D25/20 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F05D2220/76 ,  F05D2230/72 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2260/98 ,  F05D2270/304 ,  F16H57/0434 ,  F16H57/045 ,  F16H57/0471 ,  F16H57/0479

Abstract: A gas turbine engine installed on an aircraft includes a fan rotor, a turbine rotor, a gearbox, an auxiliary pump, and an electric motor. The gearbox couples the fan rotor to the turbine rotor, the turbine rotor being adapted to drive the fan rotor via the gearbox. The auxiliary pump is configured to circulate lubricating fluid in an auxiliary lubrication system and supplies the gearbox. The electric motor is configured to receive electricity when the aircraft is parked an adapted to drive the auxiliary pump such that the auxiliary pump circulates lubricating fluid while the aircraft is parked.

公开(公告)号：US20170138217A1

公开(公告)日：2017-05-18

申请号：US14943418

申请日：2015-11-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F01D21/10 ,  F02C7/06 ,  F02C3/10 ,  F01D25/18

CPC classification number: F01D21/10 ,  F01D25/18 ,  F02C3/10 ,  F02C7/06 ,  F02C7/36 ,  F05D2220/32 ,  F05D2260/40311 ,  F05D2260/606 ,  F05D2260/607 ,  F05D2260/80 ,  F05D2260/83 ,  F05D2260/98 ,  G01N15/0656 ,  G01N15/1031 ,  G01N33/2858 ,  G01N2015/0053 ,  G01N2015/1062 ,  Y02T50/675

Abstract: According to one aspect of the present disclosure, a debris monitoring system is disclosed that includes a fan, a geared architecture operatively coupled to the fan. The geared architecture includes a component having a non-ferrous metal coating. A scavenge pump is in fluid communication with the geared architecture via a lubrication sump. A non-ferrous chip detector is situated downstream of the geared architecture, but upstream of the scavenge pump. A controller is configured to determine a lubrication condition of the component based on a signal received from the non-ferrous chip detector, and command a status indicator in response thereto.

公开(公告)号：US20170122216A1

公开(公告)日：2017-05-04

申请号：US15395277

申请日：2016-12-30

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

IPC: F02C7/36 ,  F02C3/04 ,  F02C9/18 ,  F01D9/02 ,  F04D29/32 ,  F04D27/00 ,  F02K1/78 ,  F02K3/06 ,  F01D5/06

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：US20170107839A1

公开(公告)日：2017-04-20

申请号：US14887013

申请日：2015-10-19

Applicant: United Technologies Corporation

Inventor： Jorn A. Glahn ,  Frederick M. Schwarz

IPC: F01D11/02 ,  F04D29/32 ,  F01D11/04 ,  F04D29/08 ,  F02C3/04 ,  F01D5/02

CPC classification number: F01D11/025 ,  F01D5/02 ,  F01D5/082 ,  F01D11/001 ,  F01D11/02 ,  F01D11/04 ,  F02C3/04 ,  F04D29/083 ,  F04D29/321 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/50 ,  F05D2260/14 ,  F05D2260/15 ,  Y02T50/676

Abstract: Aspects of the disclosure are directed to an engine of an aircraft comprising: a first seal located forward of a disk of a turbine section of the engine, a second seal located forward of the disk of the turbine section and radially inward of the first seal relative to an axial centerline of the engine, where the first and second seals are floating, non-contact seals.

公开(公告)号：US20170051631A1

公开(公告)日：2017-02-23

申请号：US14830514

申请日：2015-08-19

Applicant: United Technologies Corporation

Inventor： William K. Ackermann ,  Clifton J. Crawley, JR. ,  Frederick M. Schwarz

IPC: F01D25/12 ,  F02C7/18 ,  F01D11/08 ,  F01D9/04 ,  F01D11/04 ,  F02C3/14 ,  F01D5/02

CPC classification number: F01D25/12 ,  F01D5/02 ,  F01D5/082 ,  F01D5/3015 ,  F01D9/041 ,  F01D11/001 ,  F01D11/04 ,  F01D11/08 ,  F02C3/14 ,  F02C7/18 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/55 ,  F16J15/442 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a bladed rotor assembly, a stator vane assembly, a fixed stator structure and a seal assembly. The bladed rotor assembly includes a rotor disk structure. The stator vane assembly is disposed adjacent the bladed rotor assembly. The fixed stator structure is connected to and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.

Abstract translation: 为旋转设备提供组件。 这些组件中的一个包括叶片转子组件，定子叶片组件，固定定子结构和密封组件。 叶片转子组件包括转子盘结构。 定子叶片组件设置在叶片转子组件附近。 固定的定子结构连接到定子叶片组件的径向上。 密封组件被构造用于密封定子结构和转子盘结构之间的间隙，其中密封组件包括非接触式密封。

公开(公告)号：US20170044992A1

公开(公告)日：2017-02-16

申请号：US15292472

申请日：2016-10-13

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph Brent Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C9/18 ,  F01D11/12 ,  F02K3/06 ,  F02K3/075 ,  F02C7/36 ,  F02C3/107

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D11/122 ,  F01D25/24 ,  F02C3/04 ,  F02C3/107 ,  F02C7/20 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F04D19/02 ,  F05B2250/283 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.