公开(公告)号：US20180355759A1

公开(公告)日：2018-12-13

申请号：US16108540

申请日：2018-08-22

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F01D25/18 ,  F02C7/06 ,  F01D25/20 ,  B01D19/00

CPC classification number: F01D25/18 ,  B01D19/0068 ,  B01D19/0073 ,  F01D25/20 ,  F02C7/06 ,  F05D2260/609 ,  Y02T50/671

Abstract: A gas turbine engine has a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system supplies oil to the gear reduction, and includes a lubricant pump to supply an air/oil mixture to an inlet of a deaerator. The deaerator includes a separator for separating oil and air, delivering separated air to an air outlet, and delivering separated oil back into an oil tank. The separated oil is first delivered into a pipe outwardly of the oil tank, and then into a location beneath a minimum oil level in the tank. Air within the oil tank moves outwardly through an air exit into the deaerator. A method of designing a gas turbine engine is also disclosed.

公开(公告)号：US20180313274A1

公开(公告)日：2018-11-01

申请号：US15498764

申请日：2017-04-27

Applicant: United Technologies Corporation

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

IPC: F02C7/36

CPC classification number: F02C7/36 ,  F02C7/32 ,  F05D2250/322 ,  F05D2260/40311

Abstract: A gas turbine engine comprises a high speed spool and a low speed spool. A low speed power takeoff is driven by the low speed spool and a high speed power takeoff is driven by the high speed spool. The low speed power takeoff drives a plurality of low speed driven accessories about low speed spool drive axes and the high speed power takeoff drives a plurality of high speed driven accessories about high speed spool drive axes. The low speed spool drive axes are generally tangential to an envelope defined about a center axis of the engine, and the high speed spool drive axes are generally tangential to an envelope defined about the center.

公开(公告)号：US20180291818A1

公开(公告)日：2018-10-11

申请号：US15484841

申请日：2017-04-11

Applicant: United Technologies Corporation

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

IPC: F02C7/32 ,  F16H1/22

Abstract: An assembly is provided for a gas turbine engine with an axial centerline. This assembly includes a gearbox, a first torque transmission apparatus and a second torque transmission apparatus. The gearbox includes a plurality of first gears and a plurality of second gears. The first gears are meshed together and respectively rotatable about parallel first gear axes. The second gears are meshed together and respectively rotatable about parallel second gear axes. Each of the first gear axes and each of the second gear axes is non-parallel with the axial centerline. The first torque transmission apparatus is configured to drive the first gears. The second torque transmission apparatus is configured to drive the second gears.

公开(公告)号：US20180291817A1

公开(公告)日：2018-10-11

申请号：US15484376

申请日：2017-04-11

Applicant: United Technologies Corporation

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

IPC: F02C7/32 ,  F02C7/18

CPC classification number: F02C7/32 ,  F02C7/185 ,  F02C7/36 ,  F05D2220/764 ,  F05D2220/768 ,  F05D2270/023

Abstract: A gas turbine engine comprises a low speed spool and a high speed spool, with each of the spools including a turbine to drive a respective one of the spools. The high speed spool rotates at a higher speed than the low speed spool. A high speed power takeoff is driven to rotate by the high speed spool, and a low speed power takeoff is driven to rotate by the low speed spool. The high speed power takeoff drives a starter generator and a permanent magnet alternator. The low speed power takeoff drives a variable frequency generator.

公开(公告)号：US10094278B2

公开(公告)日：2018-10-09

申请号：US14892103

申请日：2014-05-06

Applicant: United Technologies Corporation

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

IPC: F02C3/107 ,  F16C35/06 ,  F02C7/06 ,  F02C7/36 ,  F01D25/16 ,  F02C3/06 ,  F02K3/06 ,  F16C19/26 ,  F16C19/54 ,  F16C19/55

Abstract: A turbofan engine (20) comprises a fan (28). A fan drive gear system (60) is configured to drive the fan. A low spool comprises a low pressure turbine (50) and a low shaft (56) coupling the low pressure turbine to the fan drive gear system. An intermediate spool comprises an intermediate pressure turbine (48), a compressor (42), and an intermediate spool shaft (54) coupling the intermediate pressure turbine to the intermediate spool compressor. A combustor (45) is between a core spool compressor (44) and a high pressure turbine (46). A first (160) main bearing engages a static support (164; 164′) and a forward hub (236) of the intermediate spool. A second (162) main bearing engages the low shaft and the forward hub.

公开(公告)号：US10087850B2

公开(公告)日：2018-10-02

申请号：US15862716

申请日：2018-01-05

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  John R. Otto

IPC: F02C7/36 ,  F02C7/06 ,  F02C7/20

Abstract: A gas turbine engine includes a fan shaft arranged along an engine central axis, a frame supporting the fan shaft, a gear system rotatably coupled with the fan shaft, and a flexible coupling at least partially supporting the gear system. The flexible coupling defines, with respect to the engine central axis, a torsional stiffness TS and a lateral stiffness LS such that a ratio of TS/LS is greater than or equal to about 2.0 to reduce loads on the gear system from misalignment of the gear system with respect to the engine central axis.

公开(公告)号：US10066734B2

公开(公告)日：2018-09-04

申请号：US14960934

申请日：2015-12-07

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F16H57/04 ,  F01D25/18 ,  F02C7/36 ,  F16H1/28 ,  F01D25/16

Abstract: A gas turbine engine includes a planetary gear system including a sun gear, intermediate gears, and a ring gear. A lubricant recovery system for the planetary gear system includes fluid passages that extend through the planetary gear system. A gutter is located radially outward from the planetary gear system for collecting lubricant. At least a portion of the gutter is rigidly attached to the ring gear.

公开(公告)号：US10041408B2

公开(公告)日：2018-08-07

申请号：US14622438

申请日：2015-02-13

Applicant: United Technologies Corporation

Inventor： Daniel B. Kupratis ,  William G. Sheridan

IPC: F02C3/073 ,  F02C6/12 ,  F02C7/36 ,  F01D5/22 ,  F02C3/045 ,  F01D5/14 ,  F02K3/06 ,  F01D5/02 ,  F02C3/06 ,  F02C3/107 ,  F02K3/00 ,  F04D29/32 ,  F01D13/00 ,  F02K1/60 ,  F02K1/68

Abstract: A turbine engine is provided that includes a turbo-compressor and a combustor section. The turbo-compressor includes a compressor section and a turbine section. The combustor section is fluidly coupled between the compressor section and the turbine section. The compressor section includes a first number of stages. The turbine section includes a second number of stages that is different than the first number.

公开(公告)号：US20180073439A9

公开(公告)日：2018-03-15

申请号：US14705577

申请日：2015-05-06

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Karl L. Hasel

IPC: F02C7/36 ,  F02C7/32 ,  F02C3/06 ,  F16H1/36

CPC classification number: F02C7/36 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02C3/113 ,  F02C7/00 ,  F02C7/32 ,  F05D2210/12 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/40 ,  F05D2260/40311 ,  F16H1/28 ,  F16H1/36

Abstract: A gas turbine engine includes a fan section that includes a fan rotatable about an axis of rotation of the gas turbine engine. A speed reduction device is connected to the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A bypass ratio is greater than about 11.0.

公开(公告)号：US09879694B2

公开(公告)日：2018-01-30

申请号：US14612614

申请日：2015-02-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William G. Sheridan

IPC: F04D27/02 ,  F04D29/32 ,  F02K3/04 ,  F02C3/073 ,  F02C3/107 ,  F02C7/36 ,  F01D9/04 ,  F01D13/00 ,  F01D25/16

CPC classification number: F04D29/324 ,  F01D9/041 ,  F01D13/006 ,  F01D25/162 ,  F02C3/073 ,  F02C3/107 ,  F02C7/36 ,  F02K3/04 ,  F05D2250/311 ,  F05D2260/40311

Abstract: A gas turbine engine includes a fan section. A turbo-compressor section is connected to the fan section through a speed change mechanism.