Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan

Patent metadata

Field	Value
Publication number	US-9879561-B2
Application number	US-201514626452-A
Country	US
Kind code	B2
Filing date	Feb 19, 2015
Priority date	Aug 9, 2012
Publication date	Jan 30, 2018
Grant date	Jan 30, 2018

Abstract

A bypass turbine engine including: an inner casing, an inter-duct casing and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing; a rotary shaft including, at an upstream end, a movable fan with radial blades of which the free ends face the outer casing to compress an air flow at least in the secondary duct; a plurality of variable-pitch radial stator vanes mounted upstream of the movable fan so as to deflect the incident axial air prior to it being axially rectified by the movable fan in the secondary duct; and a system for individually adjusting the pitch of the radial vanes including a single control ring and rods for connecting the control ring to each of said radial vanes, is provided.

First claim

The invention claimed is:

1. A bypass turbine engine in which air flows circulate from upstream to downstream, the turbine engine extending axially and comprising:
an inner casing, an inter-duct casing, and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing;
a rotary shaft comprising, at an upstream end of the rotary shaft, a movable fan comprising radial blades of which free ends face the outer casing of the turbine engine so as to compress an air flow at least in the secondary duct;
at least one element mounted downstream of the movable fan;
a plurality of variable-pitch radial stator vanes mounted upstream of the movable fan, said variable-pitch radial stator vanes being configured to deflect axial incident air and the movable fan being configured to axially rectify said deflected air into the secondary duct; and
an adjusting system which individually adjusts a pitch of the variable-pitch radial stator vanes so as to allow an adaptive pitch to be provided depending on a configuration of the turbine engine,
wherein the element is substantially aligned longitudinally with a first set of the variable-pitch radial stator vanes including at least one of the variable-pitch radial stator vanes, the pitch of each variable-pitch radial stator vane of the first set of the variable-pitch radial stator vane being adjusted individually and being different from the pitch of a second set of variable-pitch radial stator vanes including all of the variable-pitch radial stator vanes not in the first set of variable-pitch radial stator vanes.

2. The turbine engine according to claim 1 , wherein the inner casing, the inter-duct casing, and the outer casing are at a radial distance from one another in the turbine engine so as to define a turbine engine having a bypass ratio that is equal to 15.

3. The turbine engine according to claim 1 , wherein a rotational speed of the free ends of the blades of the movable fan is less than 340 m/s.

4. The turbine engine according to claim 1 , wherein the plurality of variable-pitch radial stator vanes extend in a same plane which is transverse to an axis of the turbine engine.

5. The turbine engine according to claim 1 , wherein an axial distance between the plurality of variable-pitch radial stator vanes and the movable fan is between 0.1 and 10 times a mean chord of a variable-pitch radial stator vane.

6. The turbine engine according to claim 1 , wherein the blades of the movable fan extend between the inner casing and the outer casing of the turbine engine.

7. The turbine engine according to claim 1 , wherein each variable-pitch radial stator vane has an aerodynamic profile so as to accelerate flow of the incident air in accordance with a laminar flow.

8. The turbine engine according to claim 1 , wherein each variable-pitch radial stator vane has a body which is movable in rotation about a radial axis.

9. The turbine engine according to claim 1 , wherein each variable-pitch radial stator vane has a fixed body and a movable flap.

10. The turbine engine according to claim 1 , wherein the plurality of variable-pitch radial stator vanes forms a planar transverse surface at a given pitch position of each of the variable-pitch radial stator vanes.

11. The turbine engine according to claim 1 , wherein the adjusting system includes a single control ring, a first connecting rod, and a second connecting rod, a first end of the first connecting rod being connected to the control ring, a first end of the second connecting rod being connected to the first connecting rod, and a second end of the second connecting rod being connected to one of the variable-pitch radial stator vanes.

12. The turbine engine according to claim 1 , wherein the element comprises a strut.

13. The turbine engine according to claim 1 , wherein the control ring is movably mounted in rotation about a longitudinal axis of the turbine engine on one of the inner casing or the outer casing.

14. The turbine engine according to claim 13 , wherein the first connecting rod is movably mounted in rotation about a first substantially radial pivot pin, which is mounted on the control ring, and about a second substantially radial pivot pin, which is mounted on the fixed casing, a the second connecting rod is pivotally mounted about a third substantially radial pivot pin, which is connected to the one of the variable-pitch radial stator vanes and offset along the longitudinal axis in relation to a pitch pin of said one of the variable-pitch radial stator vanes, the second connecting rod being articulated to the first connecting rod so as to be able to pivot about a substantially radial hinge pin which is at a distance from the second pivot pin.

15. The turbine engine according to claim 14 , wherein said second connecting rod comprises means for modifying a first distance, between the third pivot pin and said hinge pin.

16. The turbine engine according to claim 14 , wherein the hinge pin is connected to the first connecting rod by connection means which are configured so as to be able to modify a second distance, between said hinge pin and the second pivot pin.

17. The turbine engine according to claim 14 , wherein at least one of the parameters selected from a first distance, between the third pivot pin and said hinge pin, and a second distance, between said hinge pin and the second pivot pin, is different between at least two variable-pitch radial stator vanes.

18. The turbine engine according to claim 14 , wherein the second connecting rod is substantially perpendicular to the first connecting rod for at least one position of the control ring.

19. The turbine engine according to claim 14 , wherein the second pivot pin and the pitch pin of said one of the variable-pitch radial stator vanes are located on a same side relative to the second connecting rod, in a direction of the longitudinal axis of the turbine engine.

20. The turbine engine according to claim 19 , wherein the first pivot pin is located on an opposite side relative to the second connecting rod, in the direction of the longitudinal axis of the turbine engine.

21. Method A method for adjusting the pitch of radial stator vanes of a turbine engine according to claim 14 , when carrying out a maintenance operation or an adjustment of the turbine engine, comprising:
modifying a first distance between the third pivot pin and said hinge pin.

22. The method according to claim 21 , further comprising modifying a second distance between said hinge pin and the second pivot pin.

23. The method according to claim 22 , wherein, a first position and a second position of the control ring are defined so as to correspond to a first pitch angle and a second pitch angle of the one of the variable-pitch radial stator vanes, as a result of operating conditions of said turbine engine, the method further comprising defining values of said first and second distances based on the first and second pitch angles respectively for the first and second positions of the control ring.

24. A bypass turbine engine in which air flows circulate from upstream to downstream, the turbine engine extending axially and comprising:
an inner casing, an inter-duct casing, and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing

Assignees

• Snecma

Inventors

• Lecordix Jean-Loic Herve
• Bordoni Nils
• Kubiak Guillaume Patrice

Classifications

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F02C7/042

  having variable geometry · CPC title

• F02C9/20

  by throttling; by adjusting vanes · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title