Aerial vehicle fluid control system integrated with gas turbine engine
An assembly is provided for an aerial vehicle. This assembly includes an airframe and a fluid circuit. The airframe includes a body and an airfoil projecting out from the body. The airfoil includes a first surface and a first aperture in the first surface. The fluid circuit is configured to bleed gas from a gas turbine engine mounted to the airframe to provide control gas. The fluid circuit is configured to selectively direct the control gas to the first aperture.
1. An assembly for an aerial vehicle, comprising:
an airframe including a body and an airfoil projecting out from the body, the airfoil including a first surface, a second surface, a first aperture in the first surface, and a second aperture in the second surface;
a fluid circuit configured to bleed gas through an inlet from a gas turbine engine mounted to the airframe to provide control gas, and the fluid circuit configured to selectively direct the control gas to the first aperture; and
a flow regulator,
wherein:
the fluid circuit directs the control gas to the first aperture during a first mode, and directs the control gas to the second aperture during a second mode;
the flow regulator is configured to fluidly couple the inlet to the first aperture and to fluidly decouple the inlet from the second aperture during the first mode; and
the flow regulator is configured to fluidly couple the inlet to the second aperture and to fluidly decouple the inlet from the first aperture during the second mode.
2. The assembly of claim 1 , wherein the first aperture is configured to exhaust the control gas along the first surface to change an aerodynamic profile of the airfoil using the control gas.
3. The assembly of claim 1 , wherein the fluid circuit is configured to selectively direct the control gas to the first aperture to maneuver the aerial vehicle.
4. The assembly of claim 1 , wherein
the airfoil extends laterally between the first surface and the second surface.
5. The assembly of claim 1 , wherein the flow regulator is configured to fluidly decouple the inlet from the first aperture and the second aperture during a third mode.
6. The assembly of claim 1 , wherein
the gas turbine engine includes a stationary structure and a rotating structure at least partially housed within the stationary structure;
the fluid circuit comprises a manifold with a first passage between the gas turbine engine and the airfoil, and the first passage fluidly couples the gas turbine engine and the first aperture; and
the stationary structure and the manifold are included in a monolithic body.
7. The assembly of claim 6 , wherein
the airfoil extends laterally between the first surface and the second surface; and
the manifold further comprises a second passage between the gas turbine engine and the airfoil, and the second passage fluidly couples the gas turbine engine and the second aperture.
8. The assembly of claim 7 , wherein the flow regulator is upstream of the first passage and the second passage.
9. The assembly of claim 1 , wherein
the gas turbine engine includes a stationary structure and a rotating structure at least partially housed within the stationary structure; and
the airfoil is fixedly connected to the stationary structure.
10. The assembly of claim 1 , wherein
the gas turbine engine comprises a compressor section; and
the fluid circuit is configured to bleed the gas from the compressor section to provide the control gas.
11. The assembly of claim 1 , wherein the gas turbine engine is housed within the body.
12. The assembly of claim 1 , wherein the gas turbine engine is configured to provide thrust for propelling the aerial vehicle.
13. An assembly for an aerial vehicle, comprising:
a gas turbine engine comprising a compressor section;
a control surface comprising an airfoil outside of the gas turbine engine, the airfoil including a first surface, a second surface, a first aperture in the first surface, and a second aperture in the second surface; and
a fluid circuit comprising an inlet configured to bleed gas from the compressor section to provide control gas,
the fluid circuit configured to selectively exhaust the control gas through the first aperture along the first surface during a first mode to change a first aerodynamic characteristic of the airfoil, and
the fluid circuit further configured to selectively exhaust the control gas through the second aperture along the second surface during a second mode to change a second aerodynamic characteristic of the airfoil.
14. The assembly of claim 13 , wherein
the airfoil extends laterally between the first surface and the second surface.
15. The assembly of claim 13 , wherein
the fluid circuit is further arranged with a flow regulator; and
the flow regulator is configured to fluidly couple the inlet to the first aperture during the first mode, and the flow regulator is configured to fluidly decouple the inlet from the first aperture during the second mode.
16. The assembly of claim 13 , wherein
the gas turbine engine includes a stationary structure and a rotating structure at least partially housed within the stationary structure;
the fluid circuit comprises a manifold between the gas turbine engine and the airfoil, and the manifold fluidly couples the compressor section and the first aperture; and
the stationary structure and the manifold are included in a monolithic body.
17. An assembly for an aerial vehicle, comprising:
a gas turbine engine including a stationary structure and a rotating structure at least partially housed within the stationary structure;
a control surface comprising an airfoil, the airfoil including a first surface, a second surface, a first aperture in the first surface, and a second aperture in the second surface;
a fluid circuit configured to bleed gas from the gas turbine engine through an inlet to provide control gas, the fluid circuit configured to selectively direct the control gas from the inlet to the first aperture through a manifold between the gas turbine engine and the control surface during a first mode, and the fluid circuit configured to selectively direct the control gas from the inlet to the second aperture through the manifold between the gas turbine engine and the control surface during the second mode; and
the stationary structure and the manifold included in a monolithic body.