公开(公告)号：US11448309B2

公开(公告)日：2022-09-20

申请号：US16785915

申请日：2020-02-10

Applicant: United Technologies Corporation

Inventor： Janice Jabido ,  Michael E. McCune

IPC: F16H57/04 ,  F01D15/12 ,  F01D25/18 ,  F02K3/02 ,  F16H1/28 ,  F16H57/08

Abstract: A fan drive gear system for a turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a sun gear that is rotatable about an axis, a plurality of intermediate gears driven by the sun gear, and a baffle that is disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears. The baffle includes a channel with at least one ramp portion directing lubricant.

公开(公告)号：US11073106B2

公开(公告)日：2021-07-27

申请号：US15881240

申请日：2018-01-26

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F02K3/06 ,  F02C3/107 ,  F02C7/36 ,  F02C7/20 ,  F01D15/12 ,  F01D5/06 ,  F04D19/00 ,  F04D25/04 ,  F04D29/053 ,  F04D29/32 ,  F01D9/04

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：US11015533B2

公开(公告)日：2021-05-25

申请号：US16671432

申请日：2019-11-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William G. Sheridan ,  Michael E. McCune

IPC: F02C7/36 ,  F16H1/28

Abstract: A gas turbine engine may include a high speed spool, a low speed spool, a first epicyclic gear system, and a second epicyclic gear system. Generally, the high speed spool mechanically connects a high pressure turbine to a high pressure compressor, and the low speed spool mechanically connects a low pressure turbine to at least one of a fan and a prop via the first epicyclic gear system and to a low pressure compressor via the second epicyclic gear system, according to various embodiments. The first epicyclic gear system and the second epicyclic gear system may include a common sun gear shaft.

公开(公告)号：US10801355B2

公开(公告)日：2020-10-13

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

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：US10781755B2

公开(公告)日：2020-09-22

申请号：US15943812

申请日：2018-04-03

Applicant: United Technologies Corporation

Inventor： Michael E. McCune

IPC: F02C7/36 ,  F16H1/28 ,  F01D15/12 ,  F02K3/072 ,  F16H57/00 ,  F16H1/46 ,  F02K3/04

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a compressor, a combustor, and a spool including a fan drive turbine that drives the fan through a gear reduction. The gear reduction includes at least two double helical gears in meshed engagement, each of the at least two double helical gears having a first plurality of gear teeth separated from a second plurality of gear teeth such that a first end of the first plurality of gear teeth and a first end of the second plurality of gear teeth are spaced apart by an axial distance. Each of the first plurality of gear teeth is offset a first circumferential offset distance in relation to the next gear tooth of the second plurality of gear teeth when moving in a circumferential direction relative to respective axes.

公开(公告)号：US20200291816A1

公开(公告)日：2020-09-17

申请号：US16406371

申请日：2019-05-08

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

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

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft configured to drive a fan, a support configured to support at least a portion of the fan shaft, the support defining a support transverse stiffness and a support lateral stiffness, a gear system coupled to the fan shaft, and a flexible support configured to at least partially support the gear system. The flexible support defines a flexible support transverse stiffness with respect to the support transverse stiffness and a flexible support lateral stiffness with respect to the support lateral stiffness. The input defines an input transverse stiffness with respect to the support transverse stiffness and an input lateral stiffness with respect to the support lateral stiffness.

公开(公告)号：US10753285B2

公开(公告)日：2020-08-25

申请号：US15869276

申请日：2018-01-12

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  William G. Sheridan

IPC: F16H57/08 ,  F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F02C7/32 ,  F16H57/023 ,  F16H1/28 ,  F16H57/04

Abstract: A method of assembling an epicyclic gear train according to an example of the present disclosure includes, among other things, the steps of providing a carrier having a central axis that includes spaced apart side walls and circumferentially spaced connecting structure defining mounts that interconnect the side walls, spaced apart apertures provided at an outer circumference of the carrier, gear pockets provided between the side walls and extending to the apertures, and a central opening in at least one of the walls, providing oil baffles between the side walls, the oil baffles including ends that abut the mounts, inserting a plurality of intermediate gears through the central opening, and then moving the intermediate gears radially outwardly into the gear pockets to extend into the apertures, inserting a sun gear through the central opening, and moving the plurality of intermediate gears radially inwardly to engage the sun gear.

公开(公告)号：US10563576B2

公开(公告)日：2020-02-18

申请号：US15828510

申请日：2017-12-01

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Michael E. McCune

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

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan delivering air into a bypass duct and into a core engine, a fan drive gear system having a gear carrier, and a fan shaft coupling the fan drive gear system to the fan. The core engine includes a low spool including a low pressure turbine and a low pressure shaft, and a high spool including a high pressure turbine, a compressor, and a high pressure shaft coupling the high pressure turbine to the compressor. A first bearing is forward of the fan drive gear system, and supporting said fan shaft and said fan drive gear system, and a second bearing is aft of the fan drive gear system, and supporting the fan drive gear system.

公开(公告)号：US20200025031A1

公开(公告)日：2020-01-23

申请号：US16125179

申请日：2018-09-07

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

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

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：US10539222B2

公开(公告)日：2020-01-21

申请号：US15185292

申请日：2016-06-17

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

IPC: F02C7/36 ,  F16H57/028 ,  F01D25/16 ,  F02K3/06 ,  F04D25/02 ,  F04D29/053 ,  F04D29/056 ,  F16H1/28

Abstract: A geared architecture for a gas turbine engine includes a fan shaft and a frame which supports said fan shaft. The frame defines a frame stiffness. A plurality of gears drives the fan shaft and includes a gear mesh that defines a gear mesh stiffness. A stiffness of a ring gear of the plurality of gears is less than about 20% of the gear mesh stiffness. A flexible support supports the geared architecture and defines a flexible support stiffness. An input coupling to the plurality of gears defines an input coupling stiffness. The flexible support stiffness and the input coupling stiffness are each less than about 11% of the frame stiffness.