Hybrid compressor

Patent metadata

Field	Value
Publication number	US-2016290342-A1
Application number	US-201615081419-A
Country	US
Kind code	A1
Filing date	Mar 25, 2016
Priority date	Mar 31, 2015
Publication date	Oct 6, 2016
Grant date	—

Abstract

A compressor for a gas turbine engine is disclosed. The compressor includes a first compression stage mounted for rotation about a central axis that includes a plurality of first-stage blades. The compressor also includes a second compression stage mounted along the central axis aft of the first compression stage to receive air compressed by the first compression stage. The second compression stage includes a plurality of second-stage blades.

First claim

What is claimed is:

1 . A compressor for a gas turbine engine, the compressor comprising
a first compression stage mounted for rotation about a central axis, the first compression stage including a plurality of first-stage blades, and a second compression stage mounted along the central axis aft of the first compression stage to receive air compressed by the first compression stage, the second compression stage including a plurality of second-stage blades, the second compression stage shaped to conduct air in a substantially radial direction away from the central axis and to discharge air in a substantially axial direction parallel to the central axis.

2 . The compressor of claim 1 , wherein the average exit radius of the plurality of second-stage blades is greater than the inlet tip radius of the plurality of second stage-blades.

3 . The compressor of claim 1 , wherein the average exit radius of the plurality of first stage-blades is greater than the inlet tip radius of the plurality of first-stage blades.

4 . The compressor of claim 1 , further comprising a diffuser mounted aft of an outlet of the second compression stage along the central axis, the diffuser shaped to conduct air in substantially only the axial direction parallel to the central axis.

5 . The compressor of claim 4 , wherein the diffuser comprises a first outlet guide vane aligned with the outlet of the second compression stage in the axial direction to receive air discharged in the axial direction parallel to the central axis by the outlet and to conduct air from the outlet in only the axial direction parallel to the central axis.

6 . The compressor of claim 5 , wherein the diffuser further comprises a second outlet guide vane aligned with the first outlet guide vane in the axial direction to receive air discharged in the axial direction parallel to the central axis by the first outlet guide vane and to conduct air from the first outlet guide vane in only the axial direction parallel to the central axis.

7 . The compressor of claim 6 , wherein the second outlet guide vane is spaced from the first outlet guide vane in the axial direction without a rotating component being positioned between the first and second outlet guide vanes.

8 . The compressor of claim 1 , further comprising an interstage vane mounted between the first compression stage and the second compression stage along the central axis, the interstage vane shaped to redirect air exiting the first compression stage in the axial and radial directions before the air enters the second compression stage.

9 . The compressor of claim 1 , wherein (i) the first compression stage is supported by a first shaft extending along the central axis and (ii) the second compression stage is supported by a second shaft separate from the first shaft extending along the central axis.

10 . A compressor for a gas turbine engine, the compressor comprising
a first compression stage mounted for rotation about a central axis, the first compression stage including a plurality of first-stage blades, and a second compression stage mounted along the central axis aft of the first compression stage, the second compression stage including a plurality of second-stage blades, the second-stage blades each having an inlet portion that has an inlet hub radius and an inlet tip radius, an outlet portion shaped to discharge air in a substantially axial direction parallel to the central axis that has an outlet hub radius and an outlet tip radius, and an average exit radius substantially midway between the outlet hub radius and the outlet tip radius that is greater than the inlet tip radius.

11 . The compressor of claim 10 , wherein each of the plurality of second-stage blades includes a radial-compression portion shaped to conduct air in a substantially radial direction away from the central axis.

12 . The compressor of claim 10 , wherein the inlet tip radius of the inlet portions of the second-stage blades is less than the average exit radius of the outlet portions of the second-stage blades.

13 . The compressor of claim 12 , further comprising a diffuser mounted aft of the outlet portions of the second compression stage along the central axis and shaped to conduct air in substantially only the axial direction parallel to the central axis.

14 . The compressor of claim 13 , wherein the diffuser comprises a first outlet guide vane aligned with the outlet portions of the second-stage blades in the axial direction to receive air discharged in the axial direction parallel to the central axis and to conduct air from the outlet portions in substantially only the axial direction parallel to the central axis.

15 . The compressor of claim 13 , wherein the diffuser comprises (i) a first outlet guide vane aligned with the outlet portions of the second-stage blades in the axial direction to receive air discharged from the second compression stage and to conduct air from the outlet portions in substantially only the axial direction parallel to the central axis, and (ii) a second outlet guide vane aligned with the first outlet guide vane in the axial direction to receive air discharged in the axial direction from the first outlet guide vane and to conduct air from the first outlet guide vane in substantially only the axial direction parallel to the central axis.

16 . The compressor of claim 15 , wherein the second outlet guide vane is spaced from the first outlet guide vane in the axial direction without a rotating component being positioned between the first and second outlet guide vanes.

17 . The compressor of claim 13 , further comprising an interstage vane mounted between the first compression stage and the second compression stage along the central axis, the interstage vane shaped to redirect air exiting the first compression stage in the axial and radial directions toward the second compression stage.

18 . The compressor of claim 13 , wherein (i) the first compression stage is supported by a first shaft extending along the central axis and (ii) the second compression stage is supported by a second shaft separate from the first shaft extending along the central axis.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Bryan William B

Classifications

• F04D19/028 Primary

  Layout of fluid flow through the stages · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2220/40

  in turbochargers · CPC title

• F01D5/045

  the wheel comprising two adjacent bladed wheel portions, e.g. with interengaging blades for damping vibrations · CPC title

• F01D5/048

  Form or construction · CPC title