公开(公告)号：US10605351B2

公开(公告)日：2020-03-31

申请号：US15808613

申请日：2017-11-09

Applicant: United Technologies Corporation

Inventor： William P. Sheridan ,  Michael E. McCune

IPC: F16H57/04 ,  F01D25/18 ,  F02C7/36 ,  F02C3/04 ,  F16H57/08

Abstract: A turbo fan engine includes a housing that supports a compressor section. At least one compressor hub is within the compressor section. A compressor shaft is arranged in the compressor section. An epicyclic gear train is coupled to the compressor shaft. At least one compressor hub and the compressor shaft are coupled at a common attachment point. The epicyclic gear train includes a carrier. A sun gear and intermediate gears are arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle is supported relative to the carrier and includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubricant on at least one of the sun gear and the intermediate gears.

公开(公告)号：US10590802B2

公开(公告)日：2020-03-17

申请号：US16125179

申请日：2018-09-07

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

IPC: F01D25/16 ,  F04D25/04 ,  F02C7/36 ,  F02C7/32 ,  F04D19/02 ,  F04D29/053 ,  F01D5/06 ,  F02K3/06 ,  F04D29/056 ,  F01D15/12 ,  F01D9/02 ,  F04D29/32 ,  F01D25/28

Abstract: A gas turbine engine includes a fan shaft that drives a fan that has fan blades. A fan shaft support that supports the fan shaft defines a fan shaft support transverse stiffness. A gear system is connected to the fan shaft and includes a gear mesh that defines a gear mesh transverse stiffness. A flexible support supports the gear system and defines a flexible support transverse stiffness. The flexible support transverse stiffness is less than 11% of the fan shaft support transverse stiffness and less than 8% of the gear mesh transverse stiffness.

公开(公告)号：US10577965B2

公开(公告)日：2020-03-03

申请号：US15984494

申请日：2018-05-21

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Fredercik M. Schwarz

IPC: F16H57/04 ,  F01D15/12 ,  F01D25/18 ,  F01D25/16 ,  F01D1/02 ,  F01D5/02 ,  F02C7/32 ,  F16H57/08

Abstract: A turbine engine according to an example of the present disclosure includes, among other things, a fan shaft, at least one tapered bearing mounted on the fan shaft, the fan shaft including at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing, a fan mounted for rotation on the at least one tapered bearing. An epicyclic gear train is coupled to drive the fan, the epicyclic gear train including a carrier supporting intermediate gears that mesh with a sun gear, and a ring gear surrounding and meshing with the intermediate gears, wherein the epicyclic gear train defines a gear reduction ratio of greater than or equal to 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train, the turbine section having a fan drive turbine that includes a pressure ratio that is greater than 5. The fan includes a pressure ratio that is less than 1.45, and the fan has a bypass ratio of greater than ten (10).

公开(公告)号：US10570824B2

公开(公告)日：2020-02-25

申请号：US14949273

申请日：2015-11-23

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael E. McCune

IPC: F02C7/06 ,  F01D15/08 ,  F01D15/12 ,  F01D25/20 ,  F01D21/14

Abstract: A system is provided for a turbine engine. This turbine engine system includes a rotating assembly, a bearing and a lubrication system. The bearing is configured with the rotating assembly. The lubrication system is configured to lubricate the bearing. The lubrication system includes a lubricant pump and a lubricant reservoir. The lubricant pump is mechanically coupled with and driven by the rotating assembly. The lubricant pump is configured with the lubricant reservoir so as to be at least partially submersed in lubricant contained within the lubricant reservoir.

公开(公告)号：US20190242301A1

公开(公告)日：2019-08-08

申请号：US16390348

申请日：2019-04-22

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Marc J. Muldoon

IPC: F02C7/06 ,  F16H57/08 ,  F16H57/04 ,  F01D5/02 ,  F02C3/04 ,  F02C7/36

CPC classification number: F02C7/06 ,  F01D5/02 ,  F02C3/04 ,  F02C7/36 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H57/0423 ,  F16H57/0427 ,  F16H57/0482 ,  F16H57/0486 ,  F16H57/082

Abstract: A gearbox assembly for a gas turbofan engine includes a sun gear rotatable about an axis and a plurality of intermediate gears driven by the sun gear. A baffle disposed between at least two of the plurality of intermediate gears includes a first gap distance within a first gap portion and a second gap distance within a second gap portion. The first gap portion is disposed between the baffle and one of the intermediate gears away from the meshed interface with the sun gear and the second gap portion is disposed near the interface with the sun gear. The first gap distance within the first gap portion is different than the second gap distance within the second gap portion to define a desired lubricant flow path.

公开(公告)号：US10358981B2

公开(公告)日：2019-07-23

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 ,  F02C7/36

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：US20190153887A1

公开(公告)日：2019-05-23

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 ,  F16H57/04 ,  F01D25/18 ,  F16H1/28 ,  F02K3/06

CPC classification number: F01D15/12 ,  F01D25/18 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/50 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H1/28 ,  F16H57/0479 ,  F16H57/0486

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.

公开(公告)号：US20190120084A1

公开(公告)日：2019-04-25

申请号：US16227271

申请日：2018-12-20

Applicant: United Technologies Corporation

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

IPC: F01D25/16 ,  F02K3/06 ,  F02C7/36 ,  F04D25/02 ,  F04D29/056 ,  F02C7/06 ,  F04D19/02 ,  F04D29/32 ,  F04D27/00 ,  F04D25/04 ,  F01D9/04 ,  F01D5/06 ,  F01D15/12 ,  F02C3/107 ,  F04D29/66 ,  F02C7/20

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan, and an outer housing surrounding the fan to define a bypass flow path, a compressor, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, the fan drive turbine driving the fan through the gear system, and the gear system straddle-mounted by first and second bearings. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

公开(公告)号：US20190113128A1

公开(公告)日：2019-04-18

申请号：US16166251

申请日：2018-10-22

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Lawrence E. Portlock

IPC: F16H57/04 ,  F16H57/08 ,  F01D25/18 ,  F02C7/28 ,  F16H1/28 ,  F01D5/02 ,  F16D1/076 ,  F02C7/36

CPC classification number: F16H57/0424 ,  F01D5/027 ,  F01D25/18 ,  F02C7/28 ,  F02C7/36 ,  F05D2240/55 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/40311 ,  F05D2260/98 ,  F16D1/076 ,  F16H1/28 ,  F16H57/0402 ,  F16H57/042 ,  F16H57/0421 ,  F16H57/043 ,  F16H57/0458 ,  F16H57/0482 ,  F16H57/0486 ,  F16H57/08 ,  Y10T29/49462

Abstract: An epicyclic gear train for a gas turbine engine according to an example of the present disclosure includes, among other things, a gutter having an annular channel, a sun gear rotatable about an axis, intermediary gears arranged circumferentially about and meshing with the sun gear, and a carrier supporting the intermediary gears, and a ring gear arranged about and intermeshing with the intermediary gears, the ring gear having an aperture axially aligned with the annular channel. The ring gear includes axially spaced apart walls that extend radially outward to define a passageway, and the passageway is arranged radially between the aperture and the annular channel such that the walls inhibit an axial flow of an oil passing from the aperture toward the annular channel.

公开(公告)号：US20190113003A1

公开(公告)日：2019-04-18

申请号：US16166235

申请日：2018-10-22

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

IPC: F02K3/06 ,  F02C7/36

CPC classification number: F02K3/06 ,  F02C7/36 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/4031 ,  F05D2260/40311 ,  F16H57/0479 ,  F16H57/0486

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbo fan shaft and a turbo fan supported on the fan shaft, a compressor section having compressor hubs with blades driven about an axis, and an epicyclic gear system driving the fan shaft. The gear system includes a carrier supporting intermediate gears that mesh with a sun gear, a ring gear surrounding and meshing with the intermediate gears, the ring gear including first and second portions each having an inner periphery with teeth, the first and second portions abutting one another at a radial interface, each of the first and second portions including a flange extending radially outward, and the first and second portions having grooves at the radial interface which form a hole that expels oil through the ring gear to a gutter, and an input shaft driving the fan shaft through the gear system, the input shaft connected to the sun gear.