Aircraft propulsion system with multi-direction bleed valve
An assembly is provided for an aircraft propulsion system. This assembly includes an engine core, a bypass duct and a bleed circuit. The engine core includes a compressor section, a combustor section, a turbine section and a core flowpath extending sequentially through the compressor section, the combustor section and the turbine section. The bypass duct includes a bypass flowpath outside of the engine core. The bleed circuit includes a bleed passage and a flow regulator. The bleed circuit is configured to direct bypass gas through the bleed passage from the bypass flowpath into the core flowpath when the flow regulator is in an open position. The bleed circuit is configured to cutoff gas flow through the bleed passage between the bypass flowpath and the core flowpath when the flow regulator is in a closed position.
1. An assembly for an aircraft propulsion system, comprising:
an engine core including a compressor section, a combustor section, a turbine section and a core flowpath extending sequentially through the compressor section, the combustor section and the turbine section;
a bypass duct comprising a bypass flowpath outside of the engine core; and
a bleed circuit including a bleed passage and a flow regulator;
the bleed circuit configured to direct bypass gas through the bleed passage from the bypass flowpath into the core flowpath when the flow regulator is in an open position;
the bleed circuit configured to cutoff gas flow through the bleed passage between the bypass flowpath and the core flowpath when the flow regulator is in a closed position; and
the bleed circuit configured to direct core gas through the bleed passage from the core flowpath into the bypass flowpath when the flow regulator is in a second open position.
2. The assembly of claim 1 , wherein
the flow regulator includes an outer wall and an inner wall at least partially circumscribed by the outer wall;
the outer wall includes an outer wall first aperture facing upstream within the bypass duct and an outer wall second aperture facing downstream within the bypass duct; and
the inner wall comprises an inner wall aperture, and the inner wall is configured to rotate to
the open position where the inner wall aperture is aligned with the outer wall first aperture;
the closed position where the inner wall aperture is covered by the outer wall; and
the second open position where the inner wall aperture is aligned with the outer wall second aperture.
3. The assembly of claim 1 , wherein
the compressor section includes a first compressor rotor and a second compressor rotor downstream of the first compressor rotor along the core flowpath; and
the bleed circuit is configured to direct the bypass gas into the core flowpath at a location between the first compressor rotor and the second compressor rotor when the flow regulator is in the open position.
4. The assembly of claim 1 , wherein
the compressor section includes a low pressure compressor section; and
the bleed circuit is configured to direct the bypass gas into the core flowpath at a location downstream of the low pressure compressor section when the flow regulator is in the open position.
5. The assembly of claim 1 , wherein the flow regulator is configured to move to the open position where the flow regulator opens a first aperture into the bypass duct; and
the closed position where the flow regulator closes the first aperture.
6. The assembly of claim 1 , wherein the bleed circuit further includes a scoop configured to direct the bypass gas from the bypass flowpath into the bleed circuit when the flow regulator is in the open position.
7. The assembly of claim 6 , wherein the flow regulator forms the scoop when the flow regulator is in the open position.
8. The assembly of claim 1 , further comprising:
a second bleed circuit including a second bleed passage and a second flow regulator;
the second bleed circuit configured to direct bypass gas through the second bleed passage from the bypass flowpath into the core flowpath when the second flow regulator is in an open position; and
the second bleed circuit configured to cutoff gas flow through the second bleed passage between the bypass flowpath and the core flowpath when the second flow regulator is in a closed position.
9. An assembly for an aircraft propulsion system, comprising:
an engine core including a compressor section, a combustor section, a turbine section and a core flowpath extending sequentially through the compressor section, the combustor section and the turbine section;
a bypass duct comprising a bypass flowpath outside of the engine core; and
a bleed circuit including a bleed passage and a flow regulator;
the bleed circuit configured to direct bypass gas through the bleed passage from the bypass flowpath into the core flowpath when the flow regulator is in an open position; and
the bleed circuit configured to cutoff gas flow through the bleed passage between the bypass flowpath and the core flowpath when the flow regulator is in a closed position;
wherein the flow regulator is configured to move to: the open position where the flow regulator opens a first aperture into the bypass duct, and the closed position where the flow regulator closes the first aperture;
wherein the flow regulator is configured to move to a second open position where the flow regulator opens a second aperture into the bypass duct; and
wherein the flow regulator closes the second aperture when in the closed position.
10. The assembly of claim 9 , wherein
the flow regulator closes the first aperture when in the second open position; and
the flow regulator closes the second aperture when in the open position.
11. The assembly of claim 9 , wherein the second aperture is disposed downstream of the first aperture along the bypass flowpath.
12. The assembly of claim 9 , wherein
the engine core extends along an axial centerline;
the flow regulator includes a valve element configured to open and close the first aperture; and
the valve element is configured to move axially along the axial centerline between the open position and the closed position.
13. The assembly of claim 9 , wherein
the engine core extends along an axial centerline;
the flow regulator includes a valve element configured to open and close the first aperture; and
the valve element is configured to move circumferentially about the axial centerline between the open position and the closed position.
14. The assembly of claim 9 , wherein
the engine core extends along an axial centerline;
the flow regulator includes a valve element configured to open and close the first aperture; and
the valve element is configured to rotate circumferentially about a regulator axis between the open position and the closed position, and the regulator axis is angularly offset from the axial centerline.
15. An assembly for an aircraft propulsion system, comprising:
an engine core including a compressor section, a combustor section, a turbine section and a core flowpath extending sequentially through the compressor section, the combustor section and the turbine section;
a bypass duct comprising a bypass flowpath outside of the engine core;
a bleed passage fluidly coupled with the core flowpath; and
a flow regulator configured to
fluidly couple the bleed passage with a first opening into the bypass flowpath during a first mode, and fluidly decouple the bleed passage from a second opening into the bypass flowpath during the first mode; and
fluidly couple the bleed passage with the second opening into the bypass flowpath during a second mode, and fluidly decouple the bleed passage from the first opening during the second mode.
16. The assembly of claim 15 , wherein the flow regulator is configured to fluidly decouple the bleed passage from the first opening and the second opening during a third mode.
17. The assembly of claim 15 , wherein the flow regulator comprises a two-way valve.