Cooling air bleed device in a turbine engine
View Patent ↗Air bleed device for cooling components in a turbine engine, including an annular conduit ( 18 ) having a radially internal portion swept by an airflow ( 22 ) and which comprises at least one air inlet orifice ( 20 ) formed in an upstream radial wall ( 38 ) of the conduit ( 18 ), a flap valve ( 40 ) for controlling the airflow entering through the orifice ( 20 ) and of which the flapper ( 41 ) includes a plate ( 42 ) applied against the wall ( 38 ) and capable of being moved by sliding on said wall ( 38 ) by a maneuvering member ( 50 ) mobile in translation parallel to the wall ( 38 ) between a position in which the plate ( 42 ) closes off the orifice ( 20 ) and a position in which the plate ( 42 ) opens said orifice.
1. A turbine engine cooling air bleed device for cooling components in a turbine engine, comprising:
an annular conduit formed in a housing that has a radially internal portion swept by an airflow, the annular conduit including at least one air inlet orifice; and
a flap valve that controls air entering through the orifice,
wherein the orifice is formed in an upstream radial wall of the conduit, and
wherein the flap valve includes a plate applied against said upstream radial wall, the plate being slidably movable on said upstream radial wall via a maneuvering member that is mobile in translation parallel to the upstream radial wall between a first position in which the plate covers and closes off the orifice and a second position in which the plate is moved away from the orifice such that said orifice is open.
2. The turbine engine cooling air bleed device according to claim 1 , wherein the upstream radial wall comprises at least one rail for guiding the plate of the flap valve in translation.
3. The turbine engine cooling air bleed device according to claim 1 , wherein a radially external end of the plate is attached to the maneuvering member.
4. The turbine engine cooling air bleed device according to claim 1 , wherein a downstream face of the plate is covered by a seal.
5. The turbine engine cooling air bleed device according to claim 4 , wherein the seal includes a stainless steel sheet structure inserted between graphite layers or a graphite metal screen structure.
6. The turbine engine cooling air bleed device according to claim 4 , wherein the seal is attached to the plate by edges of the seal, and
wherein the plate includes air passage orifices opening onto the seal, enabling air pressure to be applied on the seal.
7. The turbine engine cooling air bleed device according to claim 1 , wherein radially internal and external edges of the plate have a curvature substantially equal to a curvature of the annular conduit.
8. The turbine engine cooling air bleed device according to claim 1 , wherein the flap valve further includes a toothed wheel that rotates a threaded rod in an internal threaded channel of the maneuvering member, the threaded rod being held securely in translation by the housing.
9. The turbine engine cooling air bleed device according to claim 8 , wherein the flap valve further includes a disengageable connecting ring that is mounted coaxially and superimposed on the toothed wheel and is secured in rotation with the threaded rod, the connecting ring including teeth with oblique flanks that cooperate by meshing with teeth of the toothed wheel, the teeth of the toothed wheel having a conjugated shape formed at one end of the toothed wheel opposite the teeth of the connecting ring.
10. The turbine engine cooling air bleed device according to claim 9 , wherein the flap valve includes resilient return means axially pushing the teeth of the toothed wheel engaged with the teeth of the connecting ring.
11. A turbine engine, comprising:
a housing; and
the turbine engine cooling air bleed device according to claim 1 , said device being installed on the housing of the turbine engine in order to cool controlled flaps of a jet nozzle.
12. The turbine engine according to claim 11 , wherein the air bleed device includes a series of said flap valves that are distributed uniformly around an axis of the turbine engine.
13. The turbine engine according to claim 12 , further comprising a control actuator connected to the flap valves by synchronous drive means, the drive means including one of a flexible cable and a ball cable, connected in series to the flap valves.
14. A turbine engine, comprising the turbine engine cooling air bleed device according to claim 1 .
15. The turbine engine cooling air bleed device according to claim 1 , wherein the upstream radial wall is perpendicular to a central axis of the turbine engine.
16. The turbine engine cooling air bleed device according to claim 1 , wherein the upstream radial wall is perpendicular to an incoming secondary cooling airflow direction.
17. The turbine engine cooling air bleed device according to claim 8 , wherein the upstream radial wall is parallel to a radial axis of the threaded rod.