# US 10,480,348 B2 · Lubrication scavenge system for a turbine engine with counter-rotating shafts

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- Number: US 10,480,348 B2
- Document ID: US10480348B2
- Status: Granted
- Kind: B2
- Application number: 15/493,219
- Filed: 2017-04-21
- Published: 2017-11-02
- Granted: 2019-11-19
- Earliest claimed: 2016-04-29
- Assignees: ROLLS-ROYCE plc; Rolls-Royce North American Technologies Inc.
- Applicants: Rolls-Royce Corporation; Rolls-Royce North American Technologies, Inc.
- Inventors: Kerry J. Lighty; Phillip Burnside
- Web page: https://patentgrep.com/patent/US10480348B2

## CPC

- F01D 25/18: Lubricating arrangements (of machines or engines in general F01M)
- F01D 25/16: Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C)
- F02C 3/067: having counter-rotating rotors (F02C3/073 takes precedence)
- F16C 17/02: for radial load only
- F16C 33/10: Construction relative to lubrication {(lubrication in general F16N)}
- F16C 33/1045: {Details of supply of the liquid to the bearing}
- F16C 33/106: {Details of distribution or circulation inside the bearings, e.g. details of the bearing surfaces to affect flow or pressure of the liquid}
- F16H 57/0424: {Lubricant guiding means in the wall of or integrated with the casing, e.g. grooves, channels, holes}
- F05D 2260/602: Drainage
- F05D 2260/609: Deoiling or demisting
- F05D 2260/98: Lubrication
- F16C 2360/23: Gas turbine engines
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- 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)
- F16C: SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16H: GEARING
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A lubricant scavenging system for a turbine engine having a pair of concentric, counter-rotating shafts. The system comprises a lubricant sump housing having a radially inner surface, a pair of pedestal mounts each adapted to receive a bearing assembly from a respective shaft, a lubricant collection point axially disposed between the pedestal mounts, and a pair of axial channels adapted to guide lubricant toward the lubricant collection point.

## Claims

### Claim 1

A gas turbine comprising:
a high pressure shaft having a terminal portion;
a low pressure shaft, having an exposed portion extending axially beyond the terminal portion, the low pressure shaft concentric with the high pressure shaft;
an interface region proximate the terminal and exposed portions,
a sump housing radially surrounding the high pressure shaft and the low pressure shaft proximate the interface region, the sump housing comprising:
a radially inner surface;
a first pedestal mount for the terminal portion of the high pressure shaft and a second pedestal mount for the exposed portion of the low pressure shaft, each pedestal mount comprising an annular mount ring and plurality of stand-off pedestals, each pedestal mount extending radially inward from the radially inner surface of the sump housing,
an orifice located in the interface region and axially between first pedestal mount and second pedestal mount,
a first axial channel formed through first pedestal mount and a second axial channel formed through the second pedestal mount, wherein both the first axial channel and the second axial channel lead to the orifice, and a pair of turning passages formed in the sump housing that extend circumferentially around the sump and turn axially towards the orifice, wherein the turning passages are formed in part by at least a portion of the first axial channel and the second axial channel respectively, wherein the radial distance from the axis increases in each of the pair of turning passages as a function of axial proximity to the orifice.

### Claim 2 (depends on 1)

The turbine of claim 1, further comprising a recess formed in the radially inner surface of the sump housing proximate the orifice.

### Claim 3 (depends on 2)

The turbine of claim 2, wherein the recess is formed with blunt walls.

### Claim 4 (depends on 3)

The turbine of claim 3, wherein the recess is rectangular.

### Claim 5 (depends on 1)

The turbine of claim 1, further comprising a pair of blunt walls arranged transverse to lubricant flowing in the pair of turning passages.

### Claim 6 (depends on 1)

The turbine of claim 1, further comprising a wall extending radially inward from the sump housing on both sides of the interface and oriented parallel to the axial direction.

### Claim 7 (depends on 1)

The turbine of claim 1, wherein the orifice is located at the bottom of the sump housing such that gravitational forces allow the lubricant to drain through the orifice.

### Claim 8 (depends on 1)

The turbine of claim 1, wherein the sump housing further comprises a forward portion and aft portion axially disposed about a central portion, and wherein the radially inner surfaces of forward portion and aft portion having increasing radial distance from the axis as they extend axially toward the central portion.