Diffuser bleed assembly

1. An engine comprising:

a diffuser;

a bleed port; and

an integrated diffuser-bleed baffle assembly fluidly coupled between the diffuser and the bleed port, and

wherein the integrated diffuser-bleed baffle assembly is configured to flow a boundary layer air flow from the diffuser to the bleed port and function as a Helmholtz cavity.

2. The engine of claim 1 , wherein the integrated diffuser-bleed baffle assembly comprises a passage extending from an inlet to an outlet.

3. The engine of claim 2 , wherein the boundary layer air flow is configured to flow from the diffuser to the bleed port through the passage.

4. The engine of claim 2 , wherein the inlet is located at an outlet of the diffuser.

5. The engine of claim 2 , wherein the integrated diffuser-bleed baffle assembly and the passage gradually increase in dimension from the inlet to the outlet.

6. The engine of claim 2 , further comprising a baffle hole extending transversely to the passage through the integrated diffuser-bleed baffle assembly.

7. The engine of claim 1 , wherein the integrated diffuser-bleed baffle assembly is configured to flow air from an upper inner wall to the bleed port, from a lower inner wall to an inner casing, or both.

8. An integrated diffuser-bleed baffle assembly for a gas turbine engine, comprising:

a body having an inlet at a first end and an outlet at a second end;

a passage extending within the body from the inlet to the outlet; and

a baffle hole extending through the body in a direction transverse to the passage,

wherein the body and the passage gradually increase in width from the first end to the second end, and

wherein the passage is configured to bleed boundary layer flow from a diffuser to a bleed port.

9. The integrated diffuser-bleed baffle assembly of claim 8 , wherein the baffle hole is configured to function as a neck of a Helmholtz cavity.

10. The integrated diffuser-bleed baffle assembly of claim 8 , wherein the body is an annular body.

11. The integrated diffuser-bleed baffle assembly of claim 10 , wherein the annular body comprises a central opening configured to be fitted around the diffuser.

12. The integrated diffuser-bleed baffle assembly of claim 10 , wherein the passage is a plurality of passages extending in a radial direction around a central axis of the annular body.

13. The integrated diffuser-bleed baffle assembly of claim 12 , further comprising one or more baffle holes, each of the one or more baffles holes located transverse to the plurality of passages and between adjacent passages of the plurality of passages.

14. A method for bleeding air flow from a diffuser in a gas turbine engine, the method comprising:

providing a flow through the diffuser, the flow having a main flow and a boundary layer flow;

bleeding the boundary layer flow directly from a diffuser outlet to a bleed port; and

dampening an acoustic instability, with a Helmholtz cavity, in a cavity downstream of the diffuser.

15. The method of claim 14 , wherein the bleeding occurs in a passage coupled directly between the diffuser outlet and the bleed port.

16. The method of claim 14 , further comprising providing an integrated diffuser-bleed baffle assembly, the integrated diffuser-bleed baffle assembly configured to bleed the boundary layer flow directly from the diffuser outlet to the bleed port.

17. The method of claim 16 , wherein the integrated diffuser-bleed baffle assembly comprises a baffle hole configured to function as a neck of the Helmholtz cavity.

18. The method of claim 16 , further comprising fitting the integrated diffuser-bleed baffle assembly around an outer surface of the diffuser outlet.