Tailoring aircraft powerplant split line with inflatable bladder(s)
An assembly is provided for an aircraft propulsion system. This assembly includes a propulsor rotor and a flowpath wall. The propulsor rotor is rotatable about an axis. The propulsor rotor includes a plurality of propulsor blades and an inner platform. The propulsor blades are arranged circumferentially about the axis and project radially out from the inner platform. The flowpath wall is next to and downstream of the inner platform. The flowpath wall includes an inflatable bladder and a radial outer surface. The inflatable bladder is configured to change a geometry of the radial outer surface.
1. An assembly for an aircraft propulsion system, comprising:
a propulsor rotor rotatable about an axis, the propulsor rotor including a plurality of propulsor blades and an inner platform, and the plurality of propulsor blades arranged circumferentially about the axis and projecting radially out from the inner platform; and
a flowpath wall next to and downstream of the inner platform, the flowpath wall comprising an inflatable bladder and a radial outer surface, and the inflatable bladder configured to change a geometry of the radial outer surface.
2. The assembly of claim 1 , further comprising an air system fluidly coupled to an interior volume of the inflatable bladder.
3. The assembly of claim 2 , wherein the air system is configured to at least one of
direct air into the interior volume of the inflatable bladder to deform the radial outer surface in a radial outward direction; or
direct air out of the interior of the inflatable bladder to deform the radial outer surface in a radial inward direction.
4. The assembly of claim 1 , wherein, when viewed in a reference plane parallel with the axis, at least one of
the radial outer surface has a convex geometry with the inflatable bladder inflated; or
the radial outer surface has a straight line geometry with the inflatable bladder deflated.
5. The assembly of claim 1 , wherein the inflatable bladder includes a deformable face skin, a rigid backing and an interior volume radially between the deformable face skin and the rigid backing.
6. The assembly of claim 5 , wherein the deformable face skin is configured to rest radially against the rigid backing with the inflatable bladder deflated.
7. The assembly of claim 5 , wherein the deformable face skin is spaced radially from the rigid backing with the inflatable bladder deflated.
8. The assembly of claim 5 , wherein
the deformable face skin includes a polymer matrix and fiber reinforcement embedded within the polymer matrix; and
the rigid backing comprises metal.
9. The assembly of claim 1 , wherein the inflatable bladder is annular.
10. The assembly of claim 1 , wherein the propulsor rotor comprises a fan rotor.
11. The assembly of claim 1 , further comprising:
an engine core configured to drive rotation of the propulsor rotor about the axis, the engine core including a core flowpath, a compressor section, a combustor section and a turbine section;
the core flowpath extending from a core inlet into the core flowpath, through the compressor section, the combustor section and the turbine section, to a core exhaust from the core flowpath; and
the inflatable bladder disposed at the core inlet.
12. The assembly of claim 11 , wherein the inflatable bladder is arranged upstream of the core inlet.
13. The assembly of claim 11 , further comprising:
a bypass flowpath disposed outside of the engine core, the bypass flowpath extending from a bypass inlet into the bypass flowpath to a bypass exhaust from the bypass flowpath; and
a splitter downstream of the propulsor rotor, the splitter forming an outer peripheral boundary of the core inlet, and the splitter forming an inner peripheral boundary of the bypass inlet.
14. The assembly of claim 13 , wherein the flowpath wall is an inner flowpath wall and the inflatable bladder is an inner inflatable bladder, and further comprising:
an outer flowpath wall comprising an outer inflatable bladder and a radial inner surface;
the outer inflatable bladder disposed at the bypass inlet; and
the outer inflatable bladder configured to change a geometry of the radial inner surface.
15. The assembly of claim 1 , wherein the flowpath wall is an inner flowpath wall and the inflatable bladder is an inner inflatable bladder, and further comprising:
an outer flowpath wall next to an outer periphery of the propulsor rotor;
the outer flowpath wall comprising an outer inflatable bladder and a radial inner surface that is upstream of the propulsor rotor; and
the outer inflatable bladder configured to change a geometry of the radial inner surface.
16. The assembly of claim 1 , wherein the flowpath wall is a downstream flowpath wall, the inflatable bladder is a downstream inflatable bladder and the radial outer surface is a downstream radial outer surface, and further comprising:
an upstream flowpath wall next to and upstream of the inner platform;
the upstream flowpath wall comprising an upstream inflatable bladder and an upstream radial outer surface; and
the upstream inflatable bladder configured to change a geometry of the upstream radial outer surface.
17. The assembly of claim 16 , further comprising a stationary nose cone that comprises the upstream flowpath wall.
18. An assembly for an aircraft propulsion system, comprising:
a bladed rotor rotatable about an axis;
an inner flowpath wall downstream of the bladed rotor, the inner flowpath wall comprising an inner inflatable bladder and a radial outer surface, the inner inflatable bladder configured to change a geometry of the radial outer surface, and the radial outer surface forming a radial inner peripheral boundary of a flowpath; and
an outer flowpath wall axially overlapping and circumscribing the inner flowpath wall, the outer flowpath wall comprising an outer inflatable bladder and a radial inner surface, the outer inflatable bladder configured to change a geometry of the radial inner surface, and the radial inner surface forming a radial outer peripheral boundary of the flowpath.
19. An assembly for an aircraft propulsion system, comprising:
a propulsor rotor rotatable about an axis; and
a flowpath wall next to an outer periphery of the propulsor rotor, the flowpath wall comprising an inflatable bladder and a radial inner surface that is downstream of the propulsor rotor, and the inflatable bladder configured to change a geometry of the radial inner surface;
wherein, when viewed in a reference plane parallel with the axis, the radial inner surface has a convex geometry or a straight line geometry with the inflatable bladder deflated;
further comprising:
a splitter downstream of the propulsor rotor, the splitter forming an outer peripheral boundary of an inlet into a core flowpath, and the splitter forming an inner peripheral boundary of an inlet into a bypass flowpath;
at least an axial majority of the inflatable bladder is arranged upstream of the splitter.