GEARED COMPRESSOR FOR GAS TURBINE ENGINE

• US 20140150401A1
• Filed: 10/22/2013
• Published: 06/05/2014
• Est. Priority Date: 10/31/2012
• Status: Active Grant

• Current Assignee: Rolls-Royce Deutschland Limited & Company KG (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Deutschland Limited & Company KG (Rolls-Royce Holdings Plc)
• Inventors: VENTER, Gideon Daniel
• Granted Patent: US 10,138,817 B2
• Time in Patent Office: Days
• US Class Current: 60/39.45
• CPC Class Codes: F02C 3/064 the compressor having concentric stages
• CPC Class Codes: F02C 3/067 having counter-rotating rotors F02C3/073 takes precedence
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• CPC Class Codes: F02C 3/113 with variable power transmission between rotors
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: 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
• CPC Class Codes: F02K 3/04 the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type

Abstract

A booster assembly for a gas turbine engine having a first rotor assembly comprising a low pressure turbine drivingly connected to a fan via a first shaft and a second rotor assembly comprising a second turbine drivingly connected to a high pressure compressor via a second shaft. The booster assembly comprises a further compressor arranged to be disposed about said common axis between the fan and high-pressure compressor in a direction of flow and a gearing having first and second input rotors and an output rotor. The first input rotor is arranged to be driven by the first rotor assembly and the second input rotor is arranged to be driven by the second rotor assembly such that the output rotor drives the further compressor in dependence upon the difference in rotational speed between the first and second rotor assemblies.

Claims

1. A booster assembly for a gas turbine engine having a first rotor assembly comprising a low pressure turbine drivingly connected to a fan via a first shaft and a second rotor assembly comprising a second turbine drivingly connected to a high pressure compressor via a second shaft, the first and second rotor assemblies arranged to undergo relative rotation in use about a common axis, the booster assembly comprising:

a further compressor arranged to be disposed about said common axis between the fan and high-pressure compressor in a direction of flow; and

a gearing having first and second input rotors and an output rotor, the first input rotor arranged to be driven by the first rotor assembly and the second input rotor arranged to be driven by the second rotor assembly such that the output rotor drives the further compressor in dependence upon the difference in rotational speed between the first and second rotor assemblies.

2. A booster assembly according to claim 1, wherein the further compressor rotates at a speed greater than that of the first rotor assembly but lower than that of the second rotor assembly.

3. A booster assembly according to claim 1, wherein the gearing comprises an epicyclic gearing.

4. A booster assembly according to claim 3, wherein the output rotor comprises a planet gear carrier or sun gear of the epicyclic gearing.

5. A booster assembly according to claim 3, wherein the first input rotor or second input rotor comprises a ring gear.

6. A booster assembly according to claim 1, wherein the first or second input rotor comprises an extension portion of the respective first or second shaft.

7. A booster assembly according to claim 1, wherein the first or second input rotor is connected to the respective first or second shaft by an intermediate wall or arm which is angled with respect to the common axis.

8. A booster assembly according to claim 1, wherein the output rotor of the gearing is drivingly connected to an electrical machine.

9. A booster assembly according to claim 8, wherein the electrical machine is driven by the output rotor in a generator mode of operation and/or is arranged to drive the output rotor in a starter motor mode of operation.

10. A booster assembly according to claim 8, wherein the output rotor may be connected to or else integral with a rotor of the electrical machine.

11. A booster assembly according to claim 10, wherein the electrical machine rotor comprises one or more magnets.

12. A booster assembly according to claim 8, wherein the electrical machine is disposed about the common axis.

13. A booster assembly according to claim 8, further comprising a brake for any or any combination of the first rotor assembly, second rotor assembly, the first input rotor and/or the second input rotor.

14. A gas turbine engine comprising:

a first rotor assembly comprising a low pressure turbine drivingly connected to a fan via a first shaft;

a second rotor assembly comprising a second turbine drivingly connected to a high pressure compressor via a second shaft, the first and second rotor assemblies arranged to undergo relative rotation in use about a common axis, and

a booster assembly having;

a further compressor arranged to be disposed about said common axis between the fan and high-pressure compressor in a direction of flow; and

a gearing having first and second input rotors and an output rotor, the first input rotor arranged to be driven by the first rotor assembly and the second input rotor arranged to be driven by the second rotor assembly such that the output rotor drives the further compressor in dependence upon the difference in rotational speed between the first and second rotor assemblies.