Bleed-off assembly intake device for an aircraft propulsion system

1 . An aircraft propulsion system comprising:

a casing extending circumferentially about an axis of the aircraft propulsion system, the casing including an inner radial side, the inner radial side forming and circumscribing an annular cavity;

a compressor is disposed about the axis, the compressor is configured to direct a compressed air flow into and through the annular cavity in an air flow direction; and

an assembly including an intake device disposed on the casing, the intake device including a particle separator body and an air conduit,

the particle separator body is disposed at the inner radial side, the particle separator body extending from an upstream end to a downstream end in the air flow direction, the particle separator body extending between and to a first lateral side and a second lateral side, the first lateral side and the second lateral side are disposed at the inner radial side, the particle separator body forming an interior surface and an exterior surface, the interior surface forming an inlet cavity of the intake device, the inlet cavity having an inlet opening at the downstream end, the exterior surface forming an airfoil of the particle separator body, and the airfoil having a leading edge at the upstream end, the airfoil increasing in circumferential width, relative to the axis, from the upstream end to the downstream end along the casing, and

the air conduit extending through the casing, the air conduit including a conduit inlet within the particle separator body, and the conduit inlet is disposed at the inlet cavity,

wherein the particle separator body has an arcuate shape between the first lateral side and the second lateral side, the arcuate shape of the particle separator body forms the inlet cavity between the particle separator body and the inner radial side, and the first lateral side and the second lateral side each being circumferential ends of the particle separator body.

2 . The aircraft propulsion system of claim 1 , wherein the particle separator body has a centerline extending between and to the upstream end and the downstream end, and the centerline is oriented substantially parallel to the axis.

3 . The aircraft propulsion system of claim 1 , wherein the particle separator body has a centerline extending between and to the upstream end and the downstream end, and the centerline is oriented at a tangent angle relative to an axial direction of the axis.

4 . The aircraft propulsion system of claim 1 , wherein the conduit inlet is disposed within the particle separator body closer to the upstream end than the downstream end.

5 . The aircraft propulsion system of claim 1 , wherein the conduit inlet extends about an inlet axis, and the inlet axis is perpendicular to the axis.

6 . The aircraft propulsion system of claim 1 , wherein the inlet cavity extends between and to the inlet opening and an outlet opening at the conduit inlet, and the inlet opening has a greater cross-sectional area than the outlet opening.

7 . The aircraft propulsion system of claim 1 , wherein the inlet cavity has an oblong cross-sectional shape.

8 . The aircraft propulsion system of claim 1 , wherein the assembly further includes a bleed-off valve and a pneumatic actuator, the pneumatic actuator is operably connected to the bleed-off valve to position the bleed-off valve in an open position, a closed position, or an intermediate position between the open position and the closed position, and the pneumatic actuator is connected in fluid communication with the air conduit to receive a portion of the compressed air flow from the inlet cavity for positioning the bleed-off valve.

9 . The aircraft propulsion system of claim 8 , wherein the assembly further includes a pilot valve connected in fluid communication with and between the air conduit and the pneumatic actuator.

10 . The aircraft propulsion system of claim 8 , wherein the bleed-off valve includes a bleed inlet and a bleed outlet, the bleed inlet is connected in fluid communication with the compressor by a pressure relief line, and the bleed-off valve is positionable in the open position, the closed position, or the intermediate position to direct a bleed air flow from the compressor to the bleed outlet.

11 . The aircraft propulsion system of claim 1 , further comprising a diffuser connected in fluid communication with and between the compressor and the annular cavity, and the diffuser is configured to direct the compressed air flow from the compressor to the annular cavity.

12 . The aircraft propulsion system of claim 1 , further comprising a combustor forming a combustion chamber, the annular cavity being disposed at the combustor,

wherein the particle separator body is disposed at the inner radial side on an outer radial end of the annular cavity and partially radially extends into the annular cavity from the outer radial end of the annular cavity toward the combustor.

13 . The aircraft propulsion system of claim 1 , wherein the compressed air flow into and through the annular cavity in the air flow direction is a compressed air flow gas path, the particle separator body being disposed along the compressed air flow gas path.

14 . The aircraft propulsion system of claim 1 , wherein the compressed air flow into and through the annular cavity in the air flow direction is a compressed air flow gas path, and

wherein the casing is a gas generator casing and the particle separator body is disposed on an inner radial side of the gas generator casing along the air flow gas path.

15 . A bleed-off assembly for an aircraft propulsion system, the bleed-off assembly comprising:

a casing extending circumferentially about an axis, the casing including an inner radial side, and the inner radial side forming and circumscribing an annular cavity;

a bleed-off valve and a pneumatic actuator are disposed radially outside of the casing, the pneumatic actuator is operably connected to the bleed-off valve to position the bleed-off valve in an open position, a closed position, or an intermediate position between the open position and the closed position; and

an intake device is disposed on the casing, the intake device including a particle separator body and an air conduit,

the particle separator body is disposed at the inner radial side, the particle separator body extending from an upstream end to a downstream end, the particle separator body extending between and to a first lateral side and a second lateral side, the particle separator body forming an interior surface and an exterior surface, the interior surface forming an inlet cavity of the intake device, the inlet cavity having an inlet opening at the downstream end, the exterior surface forming an airfoil of the particle separator body having a leading edge at the upstream end, the airfoil increasing in circumferential width, relative to the axis, from the upstream end to the downstream end along the casing, and

the air conduit extending through the casing, the air conduit including a conduit inlet within the particle separator body, the conduit inlet is disposed at the inlet cavity, the air conduit connecting the inlet cavity in fluid communication with the pneumatic actuator.

16 . The bleed-off assembly of claim 15 , wherein the particle separator body has a centerline extending between and to the upstream end and the downstream end, and the centerline is oriented substantially parallel to the axis.

17 . The bleed-off assembly of claim 15 , wherein the particle separator body has a centerline extending between and to the upstream end and the downstream end, and the centerline is oriented at a tangent angle relative to an axial direction of the axis.

18 . An aircraft propulsion system comprising:

a casing extending circumferentially about an axis of the aircraft propulsion system, the casing including an inner radial side, the inner radial side forming and circumscribing an annular cavity;

a compressor is disposed about the axis, the compressor is configured to direct a compressed air flow into and through the annular cavity in an air flow direction; and

an assembly including a bleed-off valve, a pneumatic actuator, and an intake device,

the pneumatic actuator is operably connected to the bleed-off valve to position the bleed-off valve in an open position, a closed position, or an intermediate position between the open position and the closed position,

the bleed-off valve including a bleed inlet and a bleed outlet, the bleed inlet is connected in fluid communication with the compressor by a pressure relief line, and the bleed-off valve is positionable in the open position, the closed position, or the intermediate position to direct a bleed air flow from the compressor to the outlet, and

the intake device including a particle separator body and an air conduit,

the particle separator body is disposed at the inner radial side, the particle separator body extending from an upstream end to a downstream end in the air flow direction, the particle separator body forming an inlet cavity and an exterior surface, the inlet cavity having an inlet opening at the downstream end, the exterior surface forming an airfoil of the particle separator body having a leading edge at the upstream end, the airfoil increasing in circumferential width, relative to the axis, from the upstream end to the downstream end along the casing, and

the air conduit extending through the casing, the air conduit including a conduit inlet within the particle separator body, the conduit inlet is disposed at the inlet cavity, and the air conduit is connected in fluid communication with the pneumatic actuator to direct a portion of the compressed air flow from the inlet cavity to the pneumatic actuator for positioning the bleed-off valve,

wherein the particle separator body has an arcuate shape between the first lateral side and the second lateral side, the arcuate shape of the particle separator body forms the inlet cavity between the particle separator body and the inner radial side, and the first lateral side and the second lateral side each being circumferential ends of the particle separator body.

19 . The aircraft propulsion system of claim 18 , wherein the particle separator body has a centerline extending between and to the upstream end and the downstream end, and the centerline is oriented substantially parallel to the air flow direction.

20 . The aircraft propulsion system of claim 18 , wherein the particle separator body has a centerline extending between and to the upstream end and the downstream end, the centerline is oriented at a tangent angle relative to an axial direction of the axis, and the centerline is oriented substantially parallel to the air flow direction.