# US 9,038,779 B2 · Geared architecture gas turbine engine with oil scavenge

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- Number: US 9,038,779 B2
- Document ID: US9038779B2
- Status: Granted
- Kind: B2
- Application number: 14/255,169
- Filed: 2014-04-17
- Published: 2015-03-05
- Granted: 2015-05-26
- Earliest claimed: 2013-08-30
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Michael E. McCune; Zachary R. Nado
- Web page: https://patentgrep.com/patent/US9038779B2

## CPC

- F16H 57/0423: {Lubricant guiding means mounted or supported on the casing, e.g. shields or baffles for collecting lubricant, tubes or pipes}
- F02C 3/107: with two or more rotors connected by power transmission
- F02C 7/36: Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H)
- F16H 57/0479: {Gears or bearings on planet carriers}
- F16H 57/0482: {Gearings with gears having orbital motion}
- F05D 2260/4031: as in toothed gearing
- F05D 2260/40311: of the epicyclical, planetary or differential type
- F05D 2260/98: Lubrication
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F16H: GEARING
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A gas turbine engine includes a geared architecture with a multiple of intermediate gears, and a baffle with an oil scavenge scoop adjacent to each of the multiple of intermediate gears. A geared architecture and method are also disclosed.

## Claims

### Claim 1

A gas turbine engine, comprising:
a geared architecture with a multiple of intermediate gears; and
a baffle with an oil scavenge scoop adjacent to each of the multiple of intermediate gears.

### Claim 2 (depends on 1)

The gas turbine engine as recited in claim 1, wherein each of the multiple of intermediate gears and the baffles are mounted to a rotational carrier.

### Claim 3 (depends on 1)

The gas turbine engine as recited in claim 1, wherein the oil scavenge scoop includes a scavenge passage with an inner scavenge passage wall, an outer scavenge passage wall and a radial outer scavenge passage wall therebetween.

### Claim 4 (depends on 3)

The gas turbine engine as recited in claim 3, wherein the radial outer scavenge passage wall defines a ramp surface.

### Claim 5 (depends on 4)

The gas turbine engine as recited in claim 4, further comprising an exit through a baffle end wall adjacent to the radial outer passage.

### Claim 6 (depends on 5)

The gas turbine engine as recited in claim 5, wherein the radial outer scavenge passage wall defines a peak.

### Claim 7 (depends on 6)

The gas turbine engine as recited in claim 6, further comprising a first exit through a first baffle end wall adjacent to the radial outer passage and a second exit through a second baffle end wall adjacent to the radial outer passage.

### Claim 8 (depends on 3)

The gas turbine engine as recited in claim 3, further comprising a flow splitter between the inner scavenge passage wall and the outer scavenge passage wall.

### Claim 9 (depends on 8)

The gas turbine engine as recited in claim 8, wherein the inner scavenge passage wall and the outer scavenge passage wall define curved surfaces.

### Claim 10 (depends on 9)

The gas turbine engine as recited in claim 9, wherein the inner scavenge passage wall and the outer scavenge passage wall generally follow a curved outer wall that generally follows a diameter of the adjacent intermediate gear.

### Claim 11 (depends on 10)

The gas turbine engine as recited in claim 10, wherein the inner scavenge passage wall is of a different length than the outer scavenge passage wall.

### Claim 12 (depends on 1)

The gas turbine engine as recited in claim 1, wherein the oil baffle defines a multiple of oil jets.

### Claim 13 (depends on 12)

The gas turbine engine as recited in claim 12, wherein the multiple of oil jets are directed toward a gear mesh between one of the multiple of intermediate gears and a sun gear.

### Claim 14 (depends on 1)

The gas turbine engine as recited in claim 1, wherein the geared architecture includes a planetary gear system.

### Claim 15 (depends on 14)

The gas turbine engine as recited in claim 14, including a turbine section including a fan drive turbine coupled to drive a fan through the geared architecture and at least one other turbine forward of the fan drive turbine.

### Claim 16 (depends on 15)

The gas turbine engine as recited in claim 15, wherein the geared architecture includes an efficiency greater than about 98%.

### Claim 17 (depends on 15)

The gas turbine engine as recited in claim 15, wherein the fan includes a fan pressure ratio of less than about 1.45.

### Claim 18 (depends on 1)

The gas turbine engine as recited in claim 1, wherein the gas turbine engine is a high bypass engine having a bypass ratio greater than about ten (ten).

### Claim 19

A geared architecture for a gas turbine engine, comprising:
a sun gear defined along an axis;
a ring gear rotationally fixed around the axis;
a multiple of planet gears in meshed engagement with the sun gear and the ring gear;
a carrier for rotating about the axis and for rotationally supporting the multiple of planet gears; and
a multiple of baffles mounted to the carrier, each of the baffles includes a multiple of oil nozzles directed toward a gear mesh between one of the multiple of planet gears and the sun gear and an oil scavenge scoop upstream of the multiple of oil nozzles with respect to the gear mesh.

### Claim 20 (depends on 19)

The geared architecture as recited in claim 19, wherein the oil scavenge scoop includes a scavenge passage with an inner scavenge passage wall, an outer scavenge passage wall and a radial outer scavenge passage wall therebetween.

### Claim 21 (depends on 20)

The geared architecture as recited in claim 20, wherein the radial outer scavenge passage wall defines a ramp surface toward the exit.

### Claim 22 (depends on 20)

The geared architecture as recited in claim 20, wherein the radial outer scavenge passage wall defines a peak.

### Claim 23 (depends on 20)

The geared architecture as recited in claim 20, further comprising a flow splitter between the inner scavenge passage wall and the outer scavenge passage wall.

### Claim 24 (depends on 20)

The geared architecture as recited in claim 20, wherein the inner scavenge passage wall is of a different length than the outer scavenge passage wall.

### Claim 25 (depends on 19)

The geared architecture as recited in claim 19, wherein the geared architecture provides a speed reduction between a turbine section and a fan section of greater than about 2.3.

### Claim 26

A method of designing a geared architecture for a turbine engine, the method comprising:
defining a sun gear for rotation about an engine central axis;
defining a ring gear to be rotationally fixed around the engine central axis;
defining a multiple of planet gears in meshed engagement with the sun gear and the ring gear;
configuring a carrier to rotate about the central axis and to rotationally support the multiple of planet gears; and
defining the carrier to include at least one baffle with multiple oil nozzles directed toward a gear mesh engagement between one of the multiple of planet gears and the sun gear, and an oil scavenge scoop upstream of the multiple of oil nozzles relative to the gear mesh.

### Claim 27 (depends on 26)

The method of designing a geared architecture as recited in claim 26, wherein configuring the oil scavenge scoop includes defining a scavenge passage with an inner scavenge passage wall, an outer scavenge passage wall and a radial outer scavenge passage wall therebetween.

### Claim 28 (depends on 27)

The method of designing a geared architecture as recited in claim 27, including configuring the radial outer scavenge passage wall to define a ramp surface toward the exit.

### Claim 29 (depends on 27)

The method of designing a geared architecture as recited in claim 27, including configuring the radial outer scavenge passage wall to define a peak.

### Claim 30 (depends on 26)

The method of designing a geared architecture as recited in claim 26, including configuring the geared architecture to provide a speed reduction between a turbine section and a fan section of greater than about 2.3.