公开(公告)号：US10995673B2

公开(公告)日：2021-05-04

申请号：US15410113

申请日：2017-01-19

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Hung Duong ,  Jonathan F. Zimmitti ,  William G. Sheridan ,  Michael E. McCune ,  Brian Merry

IPC: F02C7/32 ,  F02C3/06 ,  F02C7/18 ,  F02C7/36 ,  F02C7/268 ,  F01D15/10 ,  F01D25/12 ,  F16H1/22 ,  H02K7/116 ,  H02K7/18 ,  F01D15/12 ,  F02C7/275

Abstract: An exemplary gas turbine engine assembly includes a first spool having a first turbine operatively mounted to a first turbine shaft, and a second spool having a second turbine operatively mounted to a second turbine shaft. The first and second turbines are mounted for rotation about a common rotational axis within an engine static structure. The first and second turbine shafts are coaxial with one another. First and second towershafts are respectively coupled to the first and second turbine shafts. An accessory drive gearbox has a set of gears. A compressor is driven by the first towershaft. The engine assembly further includes a starter generator assembly, and a transmission coupling the starter generator assembly to the first set of gears. The transmission is transitionable between a first mode where the starter generator assembly is driven at a first speed relative to the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft.

公开(公告)号：US10829831B2

公开(公告)日：2020-11-10

申请号：US15411355

申请日：2017-01-20

Applicant: United Technologies Corporation

Inventor： Dilip M. Shah ,  Herbert A. Chin ,  John Joseph Marcin ,  Paul L. Reynolds ,  Gabriel L. Suciu ,  Paul D. Genereux ,  Carl E. Kelly

IPC: C21D8/10 ,  C21D9/08 ,  C22F1/10 ,  C22C38/00 ,  F01D5/02 ,  C30B29/52 ,  C30B33/02 ,  C22C19/03 ,  B22D27/04 ,  C21D1/26 ,  C22C19/05

Abstract: High modulus turbine shafts and high modulus cylindrical articles are described as are the process parameters for producing these shafts and cylindrical articles. The shafts/articles have a high Young's modulus as a result of having high modulus crystal texture along the longitudinal axis of the shaft/article. The shafts are produced from directionally solidified seeded single crystal cylinders that are axisymmetrically hot worked before a limited recrystallization process is carried out at a temperature below the recrystallization temperature of the alloy. The disclosed process produces an intense singular texture and results in shaft or cylindrical article with a Young's modulus that is at least 40% greater than that of conventional nickel or iron alloys or conventional steels.

公开(公告)号：US10774752B2

公开(公告)日：2020-09-15

申请号：US15089806

申请日：2016-04-04

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  William K. Ackermann ,  Harold W. Hipsky

IPC: F02C9/00 ,  F02C9/18 ,  F02C3/04 ,  F02C7/06 ,  F02C7/32 ,  B64D13/06 ,  F02C6/08

Abstract: An environmental control system for an aircraft includes a higher pressure tap to be associated with a higher compression location in a main compressor section associated with an aircraft engine, and a lower pressure tap to be associated with a lower pressure location in the main compressor section associated with the aircraft engine. The lower pressure location being at a lower pressure than said higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A turbine outlet receives airflow exhausted from the turbine section. A compressor outlet receives airflow exhausted from the compressor section. A combined outlet receives airflow from the turbine outlet and the compressor outlet intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft. A buffer air outlet communicates airflow to an engine buffer air system. The buffer air outlet receives airflow supplied to the turbocompressor. A gas turbine engine is also disclosed.

公开(公告)号：US20200256431A1

公开(公告)日：2020-08-13

申请号：US16274332

申请日：2019-02-13

Applicant: United Technologies Corporation

Inventor： Hung Duong ,  Marc J. Muldoon ,  Gabriel L. Suciu

IPC: F16H3/00 ,  F16H3/02 ,  F02C7/32 ,  F02K3/06

Abstract: An auxiliary gearbox has a low speed input shaft driving a first plurality of accessories. A high speed input shaft drives a second plurality of accessories. The first plurality of accessories rotating about a first set of rotational axes, which are parallel to each other and perpendicular to a first plane. The second plurality of accessories rotating about a second set of rotational axes, which are parallel to each other and perpendicular to a second plane. The first and second planes extending in opposed directions away from a drive input axis of the high speed input shaft and the low speed input shaft. The low speed input shaft drives a variable speed transmission. A gas turbine engine is also disclosed.

公开(公告)号：US10711631B2

公开(公告)日：2020-07-14

申请号：US14976876

申请日：2015-12-21

Applicant: United Technologies Corporation

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

IPC: F01D1/02 ,  F01D17/10 ,  F01D7/00 ,  F01D5/02 ,  F01D9/04 ,  F01D25/24 ,  F02C3/107 ,  F02C3/14

Abstract: A turbine engine such as a pusher fan engine is provided. This turbine engine includes a nacelle with a bypass flowpath. A fan rotor is configured to propel air out of the bypass flowpath. A plurality of guide vanes are configured to direct the air to the fan rotor.

公开(公告)号：US10443508B2

公开(公告)日：2019-10-15

申请号：US14967446

申请日：2015-12-14

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Michael G. McCaffrey

IPC: F02C7/18 ,  F02C7/32 ,  F02C7/36 ,  F02C9/18 ,  F01D17/10 ,  F01D25/12 ,  F02C7/143 ,  F04D29/28

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor, and at least one more upstream compressor. A turbine section has a high pressure turbine. A tap line taps air from at least one of the more upstream compressors 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 bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions. An intercooling system is also disclosed.

公开(公告)号：US10443429B2

公开(公告)日：2019-10-15

申请号：US15111553

申请日：2015-01-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Federico Papa

IPC: F02C7/18 ,  F01D17/14 ,  F01D25/26 ,  F02C3/04 ,  F02C9/18

Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.

公开(公告)号：US20190309705A1

公开(公告)日：2019-10-10

申请号：US15945907

申请日：2018-04-05

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02K5/00 ,  F04D19/02 ,  F04D25/06

Abstract: A boundary layer ingestion engine includes a fan section configured to extend into a boundary layer of a full annulus of an aft end of a fuselage of an aircraft. The fan section includes a first fan stage and a second fan stage. The boundary layer ingestion engine also includes a differential planetary gear system is operable to transform rotation of an input shaft into counter rotation of a first shaft coupled to the first fan stage and a second shaft coupled to the second fan stage. The boundary layer ingestion engine further includes a motor operable to drive rotation of the input shaft.

公开(公告)号：US10428740B2

公开(公告)日：2019-10-01

申请号：US15373072

申请日：2016-12-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C7/36 ,  B64D27/16 ,  B64D27/00 ,  B64D27/14 ,  B64D35/00 ,  F02K3/04 ,  B64D33/02

Abstract: A propulsion system for an aircraft has at least two fans with each fan having a fan drive shaft. A turboshaft gas turbine engine drives each of the at least two fans. The turboshaft engine drives an output shaft which drives a gear to, in turn, engage to drive a gear on a first intermediate shaft extending from the turboshaft gas turbine engine in a rearward direction toward an intermediate fan drive shaft. The intermediate fan drive shaft drives the fan drive shaft, and the at least two first intermediate drive shafts extending over a distance that is greater in an axial dimension defined between the turboshaft gas turbine engine and the fan than it is in a width dimension defined between the at least two fans.

公开(公告)号：US10421554B2

公开(公告)日：2019-09-24

申请号：US14874560

申请日：2015-10-05

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Wesley K. Lord ,  Alan H. Epstein ,  Steven M. O'Flarity

IPC: B64D35/06 ,  B64D27/20 ,  B64D27/14

Abstract: A drive arrangement for an aircraft comprises a pair of propulsor units each having a fan and a fan shaft for driving the fan. A core engine has a turbine driving a core engine shaft. A mechanical connection connects the core engine shaft to drive the fan shafts for each of the propulsor units. An aircraft also has such an arrangement.