Split axial-centrifugal compressor

Patent metadata

Field	Value
Publication number	US-10329943-B2
Application number	US-201514857196-A
Country	US
Kind code	B2
Filing date	Sep 17, 2015
Priority date	Nov 18, 2014
Publication date	Jun 25, 2019
Grant date	Jun 25, 2019

Abstract

A gas turbine engine including a compressor, a turbine, and a variable-ratio unit is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The variable-ratio unit is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

First claim

What is claimed is:

1. A gas turbine engine comprising
a compressor including an axial compression stage and a centrifugal compression stage arranged aft of the axial compression stage along an engine axis,
a turbine arranged aft of the centrifugal compression stage and coupled to the compressor to drive rotation of the axial compression stage and the centrifugal compression stage about the engine axis, and
a variable-ratio unit coupled to the turbine and the compressor, the variable-ratio unit configured to transmit rotational power generated by the turbine about the engine axis to the axial compression stage to drive rotation of the axial compression stage at various speeds offset from a turbine speed,
wherein the axial compression stage has an outlet radius and the centrifugal compression stage has an inlet radius that is about equal to the outlet radius of the axial compression stage to facilitate a smooth transition of air from the axial compression stage to the centrifugal compression stage, the centrifugal compression stage is coupled to the turbine for common rotation therewith about the engine axis, and the variable-ratio unit is arranged forward of the axial compression stage about the engine axis.

2. The gas turbine engine of claim 1 , wherein the variable-ratio unit is included in an infinitely variable transmission.

3. The gas turbine engine of claim 2 , wherein the variable-ratio unit includes one of a toroidal variator and a planetary ball variator.

4. The gas turbine engine of claim 1 , further comprising a thrust bearing supporting a portion of the variable-ratio unit and arranged forward of the axial compression stage.

5. A compressor comprising
an axial compression stage having an axial inlet and an axial outlet,
a centrifugal compression stage having a centrifugal inlet and a centrifugal outlet, and
a variable-ratio unit adapted to receive rotational power and distribute the rotational power between the axial compression stage and the centrifugal compression stage, the variable-ratio unit including an input and an output, the output coupled between the input and one of the axial compression stage and the centrifugal compression stage,
wherein the centrifugal inlet is arranged to receive compressed air discharged from the axial outlet and has a first area about equal to a second area of the axial outlet, the axial compression stage is arranged forward of the centrifugal compression stage, and the variable-ratio unit is arranged forward of the axial compression stage.

6. The compressor of claim 5 , wherein the variable-ratio unit is included in an infinitely variable transmission.

7. The compressor of claim 6 , wherein the variable-ratio unit includes one of a toroidal variator and a planetary ball variator.

8. The compressor of claim 5 , further comprising a thrust bearing being arranged forward of the axial compression stage and supporting a portion of the variable-ratio unit.

9. The compressor of claim 5 , further comprising a second variable-ratio unit, the second variable-ratio unit including an input and an output, the output coupled between the input and the other of the axial compression stage and the centrifugal compression stage.

10. The compressor of claim 9 , further comprising (i) a first thrust bearing supporting a portion of the variable-ratio unit and (ii) a second thrust bearing supporting a portion of the second variable-ratio unit.

11. The compressor of claim 9 , wherein each of the variable-ratio unit and the second variable-ratio unit is included in an infinitely variable transmission.

12. The compressor of claim 10 , wherein each of the variable-ratio unit and the second variable-ratio unit includes one of a toroidal variator and a planetary ball variator.

13. A gas turbine engine comprising
a compressor including an axial compression stage and a centrifugal compression stage arranged aft of the axial compression stage along an engine axis,
a turbine arranged aft of the centrifugal compression stage, the turbine including a single turbine stage coupled to each of the axial compression stage and the centrifugal compression stage to drive rotation of each of the axial compression stage and the centrifugal compression stage about the engine axis, and
a variable-ratio unit coupled to the turbine and the compressor, the variable-ratio unit configured to transmit rotational power generated by the turbine about the engine axis to at least one of the axial compression stage and the centrifugal compression stage to drive rotation of the at least one of the axial compression stage and the centrifugal compression stage at various speeds offset from a turbine speed.

14. The gas turbine engine of claim 13 , wherein the variable-ratio unit is arranged forward of the axial compression stage about the engine axis.

15. The gas turbine engine of claim 14 , wherein the axial compression stage is coupled to the turbine through the variable-ratio unit for rotation about the engine axis at the various speeds offset from the turbine speed.

16. The gas turbine engine of claim 15 , further comprising a thrust bearing supporting a portion of the variable-ratio unit and arranged forward of the axial compression stage.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp

Inventors

• Eifert Andrew J
• Heathco Craig E
• Cedoz Robert W
• Duge Robert T

Classifications

• F02C7/36 Primary

  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 title

• F04D25/04

  the pump being fluid-driven {(pumps driven by exhaust gases F02B37/00, F02B39/00; turbochargers F02C6/12)} · CPC title

• F01D15/12 Primary

  Combinations with mechanical gearing (driven by multiple engines F01D13/00) · CPC title

• F05D2260/403

  through the shape of the drive components · CPC title

• F04D25/02

  Units comprising pumps and their driving means · CPC title