公开(公告)号：US20190017445A1

公开(公告)日：2019-01-17

申请号：US16025022

申请日：2018-07-02

Applicant: United Technologies Corporation

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

IPC: F02C7/36 ,  F02K3/06 ,  F02C9/18 ,  F01D11/12 ,  F01D5/06 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D19/02 ,  F02K3/075 ,  F02C3/107

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including an array of fan blades rotatable about an engine axis, a compressor including a first compressor section and a second compressor section, the second compressor section including a second compressor section inlet with a compressor inlet annulus area, a fan duct including a fan duct annulus area outboard of the second compressor section inlet, and a turbine having a first turbine section driving the first compressor section, a second turbine section driving the fan through an epicyclic gearbox, the second turbine section including blades and vanes, and wherein the second turbine section defines a maximum gas path radius and the fan blades define a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.6.

公开(公告)号：US10107191B2

公开(公告)日：2018-10-23

申请号：US14964727

申请日：2015-12-10

Applicant: United Technologies Corporation

Inventor： Jonthan Gilson ,  Burce L. Morin ,  Ramons A. Reba ,  David A. Topol ,  Wesley K. Lord

IPC: F01D9/04 ,  F02C3/107 ,  F02K3/06 ,  F04D29/54 ,  F04D29/66 ,  F01D25/16

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.

公开(公告)号：US20180298829A1

公开(公告)日：2018-10-18

申请号：US15490155

申请日：2017-04-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Wesley K. Lord ,  Matthew R. Feulner ,  Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C9/18 ,  F02K3/06 ,  B64D27/14 ,  B64D33/02

Abstract: A gas turbine engine comprises a housing having an inlet leading to a fan rotor. A bypass door is mounted upstream of the inlet to the fan rotor, and is moveable away from a non-bypass position to a bypass position to selectively bypass boundary layer air vertically beneath the engine. An aircraft is also disclosed.

公开(公告)号：US20180155045A1

公开(公告)日：2018-06-07

申请号：US15874335

申请日：2018-01-18

Applicant: United Technologies Corporation

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

IPC: B64D35/08 ,  B64C11/00 ,  B64C21/06 ,  B64C39/00 ,  B64D35/02 ,  B64C1/06

CPC classification number: B64D35/08 ,  B64C1/068 ,  B64C5/02 ,  B64C11/006 ,  B64C21/06 ,  B64C23/02 ,  B64C39/005 ,  B64C2230/04 ,  B64D27/02 ,  B64D35/02 ,  B64D41/00 ,  F04D17/04

Abstract: A cross flow fan to be incorporated into an aircraft fuselage comprises an ingestion fan rotor to be positioned in a tail section of an aircraft fuselage to reduce boundary layer air from a top surface of the fuselage and to drive the air away from the top surface, and a drive arrangement for the ingestion fan rotor. An aircraft is also disclosed.

公开(公告)号：US09932933B2

公开(公告)日：2018-04-03

申请号：US14091862

申请日：2013-11-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Wesley K. Lord ,  Robert E. Malecki ,  Yuan J. Qiu ,  Becky E. Rose ,  Jonathan Gilson

IPC: F01D25/24 ,  F02C7/04 ,  F02K3/068

CPC classification number: F02K3/068 ,  F01D25/24 ,  F02C7/04 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/671

Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and about 0.45.

公开(公告)号：US09909530B2

公开(公告)日：2018-03-06

申请号：US14295566

申请日：2014-06-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas G Tillman ,  Wesley K. Lord

IPC: F02K1/52 ,  B64D29/04 ,  F02K1/12 ,  F02K3/06 ,  F02K1/00

CPC classification number: F02K1/52 ,  B64D29/04 ,  F02K1/002 ,  F02K1/12 ,  F02K3/06 ,  F05D2220/36 ,  F05D2250/73

Abstract: A fan section for an engine has a fan which rotates about an axis, the fan has an inlet for ingesting ambient air, and a non-axisymmetric nozzle for providing the fan with non-uniform back pressure.

公开(公告)号：US09909495B2

公开(公告)日：2018-03-06

申请号：US14600487

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Wesley K. Lord ,  Jesse M. Chandler ,  Michael Winter ,  Michael E. McCune ,  William G. Sheridan

IPC: F02C3/10 ,  F02K3/00 ,  B64D27/12 ,  B64D35/04 ,  F02K3/077 ,  F02C3/107

CPC classification number: F02C3/10 ,  B64D27/12 ,  B64D35/04 ,  F02C3/107 ,  F02K3/00 ,  F02K3/077

Abstract: A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.

公开(公告)号：US20170254268A1

公开(公告)日：2017-09-07

申请号：US15058229

申请日：2016-03-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Wesley K. Lord ,  Nathan Snape ,  Gabriel L. Suciu

IPC: F02C7/18

Abstract: A gas turbine engine component includes a heat exchange structure having an upstream end and a downstream end. A diffusing duct is associated with the upstream end. A throttle member controls air flow through the heat exchange structure, wherein the throttle member: (a) has a non-circular cross section; and (b) is mounted to the downstream end of the heat exchange structure or is mounted between the upstream end and the diffusing duct.

公开(公告)号：US20170190438A1

公开(公告)日：2017-07-06

申请号：US15378300

申请日：2016-12-14

Applicant: United Technologies Corporation

Inventor： Yuan J. Qiu ,  Steven H. Zysman ,  Robert E. Malecki ,  Wesley K. Lord

IPC: B64D33/02 ,  F02K3/06 ,  F01D25/24 ,  B64D27/10 ,  B64D29/00

CPC classification number: B64D33/02 ,  B64D27/10 ,  B64D29/00 ,  B64D2033/0273 ,  B64D2033/0286 ,  F01D25/24 ,  F02C7/04 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/70 ,  F05D2240/303 ,  F05D2250/51 ,  F05D2250/711

Abstract: A fan assembly for a gas turbine engine includes a fan including a plurality of fan blades extending radially outwardly from a fan hub to a blade tip defining a fan diameter. A nacelle surrounds the fan and defines a fan inlet upstream of the fan, relative to an airflow direction into the fan. The nacelle has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade. A ratio of inlet length to fan diameter is between 0.20 and 0.45. A nacelle inner surface defines a nacelle flowpath having a convex throat portion and a diffusion portion between the throat portion and the leading edge of the fan blade at a topmost portion of the nacelle. The throat portion has a minimum throat radius measured from a fan central axis greater than a blade tip radius.

公开(公告)号：US09644535B2

公开(公告)日：2017-05-09

申请号：US14325583

申请日：2014-07-08

Applicant: United Technologies Corporation

Inventor： Steven H. Zysman ,  Wesley K. Lord ,  Robert M. Miller ,  Oliver V. Atassi

IPC: F02C7/04 ,  F02C7/045 ,  B64D33/02

CPC classification number: F02C7/04 ,  B64D33/02 ,  B64D2033/0226 ,  F02C7/045 ,  F05D2250/324 ,  F05D2250/71 ,  F05D2270/17 ,  Y10T137/0536

Abstract: A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section.