Split axial-centrifugal compressor

Patent metadata

Field	Value
Publication number	US-2016201682-A1
Application number	US-201514857193-A
Country	US
Kind code	A1
Filing date	Sep 17, 2015
Priority date	Nov 18, 2014
Publication date	Jul 14, 2016
Grant date	—

Abstract

A gas turbine engine including a compressor, a turbine, and a transmission is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The transmission 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 transmission coupled to the turbine and the compressor, the transmission 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 at least one of the axial compression stage and the centrifugal compression stage at a first speed 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.

2 . The gas turbine engine of claim 1 , wherein (i) the centrifugal compression stage is coupled to the turbine for common rotation therewith about the engine axis, and (ii) the axial compression stage is coupled to the turbine through the transmission for rotation about the engine axis at the first speed offset from the turbine speed.

3 . The gas turbine engine of claim 2 , wherein the transmission comprises a first planetary gear set arranged forward of the axial compression stage about the engine axis.

4 . The gas turbine engine of claim 3 , further comprising a thrust bearing supporting the first planetary gear set and arranged forward of the axial compression stage.

5 . The gas turbine engine of claim 1 , wherein (i) the axial compression stage is coupled to the turbine for common rotation therewith about the engine axis, and (ii) the centrifugal compression stage is coupled to the turbine through the transmission for rotation about the engine axis at the first speed offset from the turbine speed.

6 . The gas turbine engine of claim 5 , wherein the transmission comprises a first planetary gear set arranged aft of the centrifugal compression stage about the engine axis.

7 . The gas turbine engine of claim 6 , further comprising a thrust bearing supporting the first planetary gear set and arranged aft of the centrifugal compression stage.

8 . The gas turbine engine of claim 1 , wherein (i) the axial compression stage is coupled to the turbine through the transmission for rotation about the engine axis at the first speed offset from the turbine speed, and (ii) the centrifugal compression stage is coupled to the turbine through the transmission for rotation about the engine axis at a second speed offset from the first speed and the turbine speed.

9 . The gas turbine engine of claim 8 , wherein the transmission comprises (i) a first planetary gear set arranged forward of the axial compression stage about the engine axis and (ii) a second planetary gear set arranged aft of the centrifugal compression stage about the engine axis.

10 . The gas turbine engine of claim 9 , further comprising (i) a first thrust bearing supporting the first planetary gear set and arranged forward of the axial compression stage and (ii) a second thrust bearing supporting the second planetary gear set and arranged aft of the centrifugal compression stage.

11 . 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 transmission adapted to receive rotational power and distribute the rotational power between the axial compression stage and the centrifugal compression stage, the transmission including an input shaft and a first gear set, the first gear set coupled between the input shaft 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, the centrifugal inlet has a first area, the axial outlet has a second area, and the first area is about equal to the second area.

12 . The compressor of claim 11 , wherein the first gear set is a planetary gear set arranged forward of the axial compression stage.

13 . The compressor of claim 12 , further comprising a thrust bearing supporting the first gear set and arranged forward of the axial compression stage.

14 . The compressor of claim 12 , wherein the first gear set includes a helical gear.

15 . The compressor of claim 11 , wherein (i) the axial compression stage is arranged forward of the centrifugal compression stage, and (ii) the first gear set is arranged aft of the centrifugal compression stage.

16 . The compressor of claim 11 , wherein the transmission further includes a second gear set coupled between the input shaft and the other of the axial compression stage and the centrifugal compression stage.

17 . The compressor of claim 16 , wherein each of the first and second gear sets is a planetary gear set.

18 . The compressor of claim 17 , further comprising (i) a first thrust bearing supporting the first gear set and (ii) a second thrust bearing supporting the second gear set.

19 . The compressor of claim 11 , wherein a ring gear of the first gear set is constrained against rotation about an axis.

20 . The compressor of claim 11 , wherein a carrier of the first gear set is constrained against rotation about an axis.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp

Inventors

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

Classifications

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F05D2240/52

  Axial thrust bearings · CPC title

• F04D25/028

  the driving means being a planetary gear · CPC title

• F04D17/025

  comprising axial flow and radial flow stages · CPC title

• F02C7/06

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