Vortex-injector casing for an axial turbomachine compressor

Patent metadata

Field	Value
Publication number	US-10359054-B2
Application number	US-201615184692-A
Country	US
Kind code	B2
Filing date	Jun 16, 2016
Priority date	Jun 18, 2015
Publication date	Jul 23, 2019
Grant date	Jul 23, 2019

Abstract

The present application proposes an axial turbomachine compressor comprising a rotor with at least one annular row of rotor blades, a stator casing surrounding the row of rotor blades, the casing including a device for generating counter-vortexes. During operation of the compressor, the movement of the blades creates leakage vortexes at the blade tip. The generating device in turn injects counter-vortexes rotating in the opposite direction to the leakage vortexes in order to counter the leakage vortexes. This improves the surge margin of the compressor. The present application also provides a method for controlling the stability of a turbomachine compressor by counter-vortex injection.

First claim

I claim:

1. An assembly for an axial turbomachine, comprising:
a rotor with at least one annular row of rotor blades; and
a stator casing surrounding the row of rotor blades;
wherein in operation the rotation of the rotor blades creates leakage vortexes between the casing and the rotor blades; and
wherein the casing includes a device for generating counter-vortexes at the level of the leakage vortexes, the device being designed such that the counter-vortexes rotate in the opposite direction to the rotation direction of the leakage vortexes.

2. The assembly according to claim 1 , wherein the device for generating counter-vortexes is designed such that, when in operation, the counter-vortexes have axes of rotation generally parallel to the leakage vortexes.

3. The assembly according to claim 1 , wherein the device for generating counter-vortexes comprises:
at least one orifice injection module distributed angularly about the rotor.

4. The assembly according to claim 3 , wherein the at least one injection module comprises:
at least one injection orifice arranged upstream of the row of rotor blades.

5. The assembly according to claim 3 , wherein the at least one injection module comprises:
at least one injection orifice arranged axially level the upstream half of the row of rotor blades.

6. The assembly according to claim 4 , wherein the at least one injection orifice has internal fins designed to generate a counter-vortex from a flow passing through the orifice.

7. The assembly according to claim 3 , wherein the at least one injection module comprises:
a set of injection orifices inclined in relation to one another such as to form a counter-vortex from a flow coming from one of the injection orifices in the set.

8. The assembly according to claim 3 , wherein the at least one injection module comprises:
at least one upstream injection orifice and one downstream injection orifice that are offset axially and around the circumference of the casing, the orifices being inclined in relation to one another in an axial plane.

9. The assembly according to claim 3 , wherein the at least one injection module comprises:
at least one upstream injection orifice and one downstream injection orifice that are offset axially and around the circumference of the casing, the orifices being inclined in relation to a plane perpendicular to the axis of rotation of the rotor.

10. The assembly according to claim 3 , wherein the at least one injection module comprises:
an air aspiration orifice positioned downstream of the row of blades.

11. The assembly according to claim 3 , wherein the at least one injection module comprises:
a pair of ducts each linking one injection orifice disposed upstream the blades to an aspiration orifice disposed downstream the blades.

12. The assembly according to claim 11 , wherein the ducts in the pair of ducts cross one another.

13. The assembly according to claim 1 , wherein the device for generating counter-vortexes comprises:
a one-piece block in which at least one duct is formed, the one-piece block extending along the entire axial length of the at least one annular row of rotor blades.

14. The assembly according to claim 1 , further comprising:
a control unit for generating counter-vortexes in an alternative manner depending on a frequency that is a function of the rotational speed of the rotor, and generation of a counter-vortex is triggered as a function of the proximity of a blade in relation to a generation device.

15. A turbomachine, comprising:
a rotor with at least one annular row of rotor blades; and
a stator casing surrounding the row of rotor blades;
wherein, when in operation, the movement of the rotor blades creates leakage vortexes between the casing and the rotor blades, the leakage vortexes turning helically in a first turning direction; and
wherein the casing includes a device for generating counter-vortexes at the level of the leakage vortexs, the counter-vortexes turning helically in a second turning direction which is opposed to the first turning direction.

16. The turbomachine according to claim 15 , further comprising:
a high pressure compressor; and
a low pressure compressor with a low pressure casing, the low pressure casing being the stator casing.

17. A stability control method for a turbomachine compressor, comprising:
providing a rotor with at least one annular row of rotor blades;
providing a casing surrounding the row of rotor blades, such that when the turbomachine is in operation, the movement of the blades creates leakage vortexes between the casing and the blades; and
limiting the leakage vortexes by generating counter-vortexes towards the leakage vortexes rotating in the opposite direction to the leakage vortexes.

18. The stability control method according to claim 17 , wherein the counter-vortexes generated are generated discontinuously.

19. The method according to claim 17 , wherein the counter-vortexes generated are injected in a downstream direction.

20. The method according to claim 17 , wherein the external extremities of the blades have chords inclined in relation to the axis of rotation of the rotor, and the counter-vortexes have, when generated, helical vortex axes generally parallel to the inclined chords of the external extremities of the blades.

Assignees

• Techspace Aero Sa
• Safran Aero Boosters Sa

Inventors

• Hiernaux Stéphane

Classifications

• F01D11/14

  Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing (rotors with blades adjustable in operation F01D7/00) · CPC title

• F01D11/10

  using sealing fluid, e.g. steam · CPC title

• F01D11/04

  using sealing fluid, e.g. steam · CPC title

• F05D2240/55

  Seals · CPC title

• F04D29/526

  Details of the casing section radially opposing blade tips (ducts F04D29/545) · CPC title