公开(公告)号：US10605173B2

公开(公告)日：2020-03-31

申请号：US16456087

申请日：2019-06-28

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：US10590853B2

公开(公告)日：2020-03-17

申请号：US15409974

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 ,  F02C7/277 ,  F02C7/22 ,  F01D15/10 ,  F01D15/08 ,  F01D15/12 ,  F01D5/06 ,  F01D25/20 ,  F01D25/16 ,  F02C7/36 ,  F01D5/02 ,  F02C7/06

Abstract: A gas turbine engine assembly includes a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, first and second towershafts respectively coupled to the first and second turbine shafts, an accessory drive gearbox mounted to the engine static structure, a hydraulic pump, and a transmission. The transmission is transitionable between a first mode where the hydraulic pump is driven at a first speed relative to a first towershaft, a second mode where the hydraulic pump is driven at a different, second speed relative to the first towershaft, and a third mode where the hydraulic pump is driven at a different, third speed relative to the first towershaft.

公开(公告)号：US10578017B2

公开(公告)日：2020-03-03

申请号：US15132639

申请日：2016-04-19

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C7/06 ,  F01D25/20 ,  F16H57/04 ,  F01M11/06 ,  F01D5/02 ,  F02C3/107 ,  F02K3/04 ,  F04D29/32 ,  F01M1/02

Abstract: A lubrication system for a gear system of a geared turbofan engine, the lubrication system includes an upper strut including an upper sump. A lower strut includes a lower sump. The upper strut and the lower strut support a gear system. A conduit extends from the upper sump within the upper strut to the lower sump within the lower strut. A lubricant collector receives lubricant exhausted from the gear system and directing the received lubricant into one of the lower sump and the upper sump. A pump in communication with the conduit for drawing lubricant from at least one of the lower sump and the upper sump and communicates lubricant to a lubricant inlet of the gear system. The pump draws lubricant from the lower sump when operating within a positive g-force environment and draws lubricant from the upper sump when operating within a negative g-force environment. A geared turbofan engine is also disclosed.

公开(公告)号：US20200056544A1

公开(公告)日：2020-02-20

申请号：US16663537

申请日：2019-10-25

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C7/06 ,  F01D25/20 ,  F02K3/06

Abstract: A gas turbine engine comprises a fan drive turbine, a fan rotor, and a gear reduction driven by the fan drive turbine to, in turn, drive the gear architecture. A main oil supply system supplies oil to components within the gear reduction, and an auxiliary oil supply system. The auxiliary oil system operates to ensure that the gear reduction will be adequately supplied with lubricant for at least 30 seconds at power should the main oil supply system fail.

公开(公告)号：US20200023982A1

公开(公告)日：2020-01-23

申请号：US16039849

申请日：2018-07-19

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz ,  William G. Sheridan ,  Glenn Levasseur

IPC: B64D27/24 ,  B64D27/10 ,  H02K7/18 ,  F01D15/10 ,  F02C6/14 ,  F02C7/36

Abstract: An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.

公开(公告)号：US10480350B2

公开(公告)日：2019-11-19

申请号：US16108540

申请日：2018-08-22

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

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

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：US20190316526A1

公开(公告)日：2019-10-17

申请号：US16456087

申请日：2019-06-28

Applicant: United Technologies Corporation

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

IPC: F02C7/32 ,  F02C7/36 ,  F02C7/18

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：US10436055B2

公开(公告)日：2019-10-08

申请号：US15386054

申请日：2016-12-21

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F01D13/00 ,  F02C3/107 ,  F02K3/04 ,  F01D25/20 ,  F02C7/36 ,  F02C6/00 ,  F02K3/077

Abstract: A propulsion system for an aircraft comprises a gas generator including a turbine driving a main drive shaft, the main drive shaft, in turn, driving at least two fan drive shafts, wherein the at least two fan drive shafts are driven on non-coaxial axes, the fan drive shaft each driving a fan rotor through a fan drive system. A fan lubrication system provides lubrication to each of the fan drive systems.

公开(公告)号：US10233773B2

公开(公告)日：2019-03-19

申请号：US14943418

申请日：2015-11-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F01D25/18 ,  F01D21/10 ,  F02C3/10 ,  F02C7/06 ,  F02C7/36 ,  G01N33/28 ,  G01N15/06 ,  G01N15/10 ,  G01N15/00

Abstract: According to one aspect of the present disclosure, a debris monitoring system is disclosed that includes a fan, a geared architecture operatively coupled to the fan. The geared architecture includes a component having a non-ferrous metal coating. A scavenge pump is in fluid communication with the geared architecture via a lubrication sump. A non-ferrous chip detector is situated downstream of the geared architecture, but upstream of the scavenge pump. A controller is configured to determine a lubrication condition of the component based on a signal received from the non-ferrous chip detector, and command a status indicator in response thereto.

公开(公告)号：US10190496B2

公开(公告)日：2019-01-29

申请号：US14776080

申请日：2014-03-14

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C3/10 ,  F02C3/107 ,  F01D25/16 ,  F02K3/06 ,  F04D25/02 ,  F04D29/059 ,  F04D29/32 ,  F02C7/36 ,  F02C7/06

Abstract: A turbofan engine (300; 600; 700) comprising a fan shaft (120) configured to rotate about an axis (500) of the engine. A fan drive gear system (60) is configured to drive the fan shaft. The fan drive gear system has a centerplane (540). A first spool comprises a high pressure turbine (326) and a high pressure compressor (324). A second spool comprises an intermediate pressure turbine (328), a lower pressure compressor, and a shaft (334) coupling the intermediate pressure turbine to the lower pressure compressor. A third spool comprises a lower pressure turbine (330) coupled to the fan drive gear system to drive the fan. The engine has a plurality of main bearings. The turbofan engine has a single stage fan. Of the main bearings, at least one is a shaft-engaging bearing engaging a driving shaft (336) coupled to the fan drive gear system. A closest (340; 640) of the shaft-engaging bearings engaging the driving shaft behind the fan drive gear system has a centerplane (550) and a characteristic radius (RB). The half angle (θ) of a virtual cone (530) intersecting the core flowpath inboard boundary at the gear system centerplane (540) and said closest of the shaft-engaging bearings at the characteristic radius (RB) is greater than about 32°. A hub-to-tip ratio (HR:FR) of the fan is less than about 0.38.