Epicyclic drive for gas turbine engine lubricant pump

Patent metadata

Field	Value
Publication number	US-11719246-B2
Application number	US-202117172546-A
Country	US
Kind code	B2
Filing date	Feb 10, 2021
Priority date	May 21, 2018
Publication date	Aug 8, 2023
Grant date	Aug 8, 2023

Abstract

A gas turbine engine includes a fan drive turbine driving a fan rotor through a main gear reduction. A primary lubricant system supplies lubricant to the main gear reduction. An auxiliary oil pump supplies oil to the main gear reduction. An auxiliary pump epicyclic gear train drives the auxiliary pump when the fan rotor is rotating in either direction. The main gear reduction is separate from the auxiliary pump epicyclic gear train.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a fan drive turbine driving a fan rotor through an epicyclic main gear reduction;
a primary lubricant system for supplying lubricant to said main gear reduction, and an auxiliary oil pump for supplying oil to said main gear reduction, and an auxiliary pump epicyclic gear train for driving said auxiliary pump when said fan rotor is rotating in either direction, said main gear reduction being separate from said auxiliary pump epicyclic gear train, said auxiliary pump epicyclic gear train including a ring gear engaged with a plurality of intermediate gears, and said plurality of intermediate gears engaged with a sun gear; and
said fan rotor being received within an outer housing, with a bypass duct being defined between said outer housing and a core housing which houses said fan drive turbine, and said fan rotor delivering air into said bypass duct as propulsion air and into said core housing, and a bypass ratio being defined as a volume of air delivered into said bypass duct divided by a volume of air delivered into said core housing, said bypass ratio being greater than 10.0, a gear ratio of said main gear reduction being greater than 2.3, and a pressure ratio measured prior to an inlet of said fan drive turbine as related to the pressure at an outlet of said fan drive turbine prior to any exhaust nozzle is greater than 5.0.

2. The gas turbine engine as set forth in claim 1 , wherein a low fan pressure ratio across a fan blade alone is less than 1.45 and a low corrected fan tip speed, which is an actual fan tip speed of said fan blade in feet per second divided by an industry standard temperature correction of [(Tram ° R)/(518.7° R)] 0.5 , being less than about 1150 ft/seconds, with both said low corrected fan tip speed and said low fan pressure ratio being measured at a cruise condition at 0.8 Mach, and 35,000 feet.

3. The gas turbine engine as set forth in claim 2 , wherein an input gear rotates when said fan rotor rotates, and in a direction of rotation of said fan rotor and engages said ring gear in said auxiliary pump epicyclic gear train, said ring gear having an outer peripheral envelope and an axis of rotation of said auxiliary pump is within said outer peripheral envelope.

4. The gas turbine engine as set forth in claim 3 , wherein said ring gear includes a first ring gear portion selectively driving a second ring gear portion through a first clutch, and said first ring gear portion driving an output shaft which is engaged to drive said auxiliary pump through a second clutch, wherein one of said first and second clutches is operable to transmit rotation when driven in a first direction of rotation, but does not transmit rotation when driven in a second direction of rotation, and the other of said first and second clutches is operable to transmit rotation when driven in said second direction of rotation, but not transmit rotation when driven in said first direction of rotation, and when said first ring gear portion drives said second ring gear portion, said second ring gear portion drives said plurality of intermediate gears to, in turn, drive said sun gear, with said sun gear rotating said output shaft.

5. The gas turbine engine as set forth in claim 4 , wherein said output shaft rotates on an output shaft axis, said auxiliary pump rotating on an auxiliary pump axis, and said input gear rotating about an input gear axis, and said input gear axis being on an opposed side of said output shaft axis relative to said auxiliary pump axis.

6. The gas turbine engine as set forth in claim 5 , wherein said first and second clutches are sprag clutches.

7. The gas turbine engine as set forth in claim 2 , wherein said ring gear includes a first ring gear portion selectively driving a second ring gear portion through a first clutch, and said first ring gear portion driving an output shaft which is engaged to drive said auxiliary pump through a second clutch, wherein one of said first and second clutches is operable to transmit rotation when driven in a first direction of rotation, but does not transmit rotation when driven in a second direction of rotation, and the other of said first and second clutches is operable to transmit rotation when driven in said second direction of rotation, but not transmit rotation when driven in said first direction of rotation, and when said first ring gear portion drives said second ring gear portion, said second ring gear portion drives said plurality of intermediate gears to, in turn, drive said sun gear, with said sun gear rotating said output shaft.

8. A gas turbine engine comprising:
a fan drive turbine driving a fan rotor through an epicyclic main gear reduction;
a primary lubricant system for supplying lubricant to said main gear reduction, and an auxiliary oil pump for supplying oil to said main gear reduction, and an auxiliary pump epicyclic gear train for driving said auxiliary pump when said fan rotor is rotating in either direction, said main gear reduction being separate from said auxiliary pump epicyclic gear train, said auxiliary pump epicyclic gear train including a ring gear engaged with a plurality of intermediate gears, and said plurality of intermediate gears engaged with a sun gear; and
said fan rotor being received within an outer housing, with a bypass duct being defined between said outer housing and a core housing which houses said fan drive turbine, and said fan rotor delivering air into said bypass duct as propulsion air and into said core housing, and a bypass ratio being defined as a volume of air delivered into said bypass duct divided by a volume of air delivered into said core housing, said bypass ratio being greater than 10.0; and
a low fan pressure ratio across a fan blade alone is less than 1.45 and a low corrected fan tip speed, which is an actual fan tip speed of said fan blade in feet per second divided by an industry standard temperature correction of [(Tram ° R)/(518.7° R)] 0.5 , being less than about 1150 ft/seconds, with both said low corrected fan tip speed and said low fan pressure ratio being measured at a cruise condition at 0.8 Mach, and 35,000 feet.

9. The gas turbine engine as set forth in claim 8 , wherein an input gear rotates when said fan rotor rotates, and in a direction of rotation of said fan rotor and engages said ring gear in said auxiliary pump epicyclic gear train, said ring gear having an outer peripheral envelope and an axis of rotation of said auxiliary pump is within said outer peripheral envelope.

10. The gas turbine engine as set forth in claim 9 , wherein said ring gear includes a first ring gear portion selectively driving a second ring gear portion through a first clutch, and said first ring gear portion driving an output shaft which is engaged to drive said auxiliary pump through a second clutch, wherein one of said first and second clutches is operable to transmit rotation when driven in a first direction of rotation, but does not transmit rotation when driven in a second direction of rotation, and the other of said first and second clutches is operable to transmit rotation when driven in said second direction of rotation, but not transmit rotation when driven in said first direction of rotation, and when said first ring gear portion drives said second ring gear portion, said second ring gear portion drives said plurality of intermediate gears to, in turn, drive said sun gear, with said sun gear rotating said output shaft.

11. The gas turbine engine as set forth in claim 10 , wherein said output shaft rotates on an output shaft axis, said auxiliary pump rotating on an auxiliary pump axis, and said input gear rotating about an input gear axis, and said input

Assignees

• Raytheon Tech Corp

Inventors

• Barger David
• Polly Joseph H

Classifications

• F04D25/028 Primary

  the driving means being a planetary gear · CPC title

• F01D25/20

  using lubrication pumps · CPC title

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F02C7/32 Primary

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F16H57/0436

  Pumps · CPC title