Gas turbine compressor bleed channel

Patent metadata

Field	Value
Publication number	US-10066633-B2
Application number	US-201414533832-A
Country	US
Kind code	B2
Filing date	Nov 5, 2014
Priority date	Nov 12, 2013
Publication date	Sep 4, 2018
Grant date	Sep 4, 2018

Abstract

A gas turbine compressor including a guide vane (1), a moving vane (2), in particular downstream, and a bleed channel (3) having an upstream channel wall (3.1), which merges into an annular space (5), an axially opposite downstream channel wall (3.2) having an inlet edge (3.3), which is rounded in particular, and a bleed channel outlet, the downstream channel wall enclosing with an axis of rotation of the compressor a first angle (α) which increases in the flow direction (x).

First claim

What is claimed is:

1. A gas turbine compressor comprising:
a guide vane;
a moving vane; and
a bleed channel having a curved upstream channel wall merging into an annular space, a curved downstream channel wall downstream axially at a distance from the upstream channel wall and having an inlet edge, and a bleed channel outlet,
the curved downstream channel wall defining, with respect to an axis of rotation of the compressor, a first angle increasing in the flow direction;
the curved upstream channel wall defining, with respect to the axis of rotation, a second angle increasing in the flow direction, the second angle increasing more than the first angle in the flow direction; and wherein:
b 1 ≤r K /5; or
0.5·[( r K +b 1 ) 2 −( r K +H ) 2 ] 1/2 ≤L≤ 1.2·[( r K +b 1 ) 2 −( r K +H ) 2 ] 1/2 or

b 1 ≥0.5· b 2 or

( b 2 −b 1 )/ s≤ 0.2

with the inlet channel height b 1 at the inlet edge, the radius of curvature of the upstream channel wall r K , the radial distance between the inlet edge and the transition of the annular space into the upstream channel wall H, the axial distance between the inlet edge and the transition of the annular space into the upstream channel wall L, the outlet channel height b 2 at the bleed channel outlet and the length of the downstream channel wall between the inlet edge and the bleed channel outlets.

2. The gas turbine compressor as recited in claim 1 wherein the first angle increases monotonically starting at the first inlet edge.

3. The gas turbine compressor as recited in claim 2 wherein the first angle increases strictly monotonically.

4. The gas turbine compressor as recited in claim 1 wherein the first angle at the bleed channel outlet is greater than 30°.

5. The gas turbine compressor as recited in claim 1 wherein the second angle increases monotonically.

6. The gas turbine compressor as recited in claim 1 wherein the curved upstream channel wall merges into the annular space upstream or downstream from a trailing edge of the guide vane.

7. The gas turbine compressor as recited in claim 1 wherein a trailing edge of at least one guide blade of the guide vane is inclined in the circumferential direction toward a suction side of the at least one guide blade in at least one radially outer third of a guide vane height or is offset axially upstream or defines, with respect to the curved upstream channel wall, an angle between 60° and 120°.

8. The gas turbine compressor as recited in claim 7 wherein the trailing edge of at least one guide blade of the guide vane is inclined in the circumferential direction toward a suction side of the at least one guide blade in at least one radially outer third of a guide vane height increasing monotonically.

9. The gas turbine compressor as recited in claim 1 wherein the moving vane is downstream of the guide blade.

10. The gas turbine compressor as recited in claim 9 wherein the inlet edge is rounded.

11. A gas turbine comprising a gas turbine compressor as recited in claim 1 .

12. An aircraft engine gas turbine comprising a gas turbine compressor as recited in claim 1 .

13. The gas turbine compressor as recited in claim 1 wherein an entire length of the curved upstream channel wall and an entire length of the curved downstream channel wall are curved.

14. The gas turbine compressor as recited in claim 1 wherein the curved downstream channel wall is curved from a rounded inlet edge to a bleed channel outlet.

Assignees

• MTU Aero Engines AG

Inventors

• Wunderer Roland

Classifications

• F04D27/023 Primary

  Details or means for fluid extraction · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F04D19/00

  Axial-flow pumps (F04D21/00 takes precedence; {pump comprising axial flow and radial flow stages F04D17/025}) · CPC title

• F04D29/541

  Specially adapted for elastic fluid pumps (F04D29/56 takes precedence) · CPC title

• F04D29/547

  having a special shape in order to influence fluid flow · CPC title