Aerodynamic intercompressor bleed ports

1. An air bleed system for a gas turbine engine, comprising:

an annular bleed case having a forward section, an aft section, ligaments spanning between and connecting an inner surface of the forward section to an inner surface of the aft section, and a series of bleed ports defined by the inner surface of the forward section, the inner surface of the aft section and the ligaments;

a bleed valve mounted to the annular bleed case; and

a manifold disposed radially outward of the ligaments and extending circumferentially about a circumference of the annular bleed case, wherein the manifold is formed between the inner surface of the forward section, the inner surface of the aft section and an outer radial surface of the ligaments, the manifold communicating with the series of bleed ports and allowing circumferential flow between each one of the series of bleed ports, and wherein the manifold is constructed such that the manifold is disposed radially inward of the bleed valve when the bleed valve is in a closed position.

2. An air bleed system for a gas turbine engine, comprising:

a compressor section; and

a bleed case having an inlet and an outlet, the inlet communicating with the compressor section; the bleed case comprising:

a forward section;

an aft section;

ligaments having a forward end, an aft end, an inner radial surface, and an outer radial surface, wherein the forward end is attached to the forward section and the aft end is attached to the aft section, whereby the ligaments span between and connect an inner surface of the forward section to an inner surface of the aft section;

bleed ports defined by the inner surface of the forward section, the inner surface of the aft section, and the ligaments, and wherein the bleed ports communicate with the inlet;

a bleed valve mounted to the bleed case; and

a manifold formed within the bleed case adjacent the outlet, wherein the manifold is formed between the inner surface of the forward section, the inner surface of the aft section and the outer radial surface of the ligaments, wherein the manifold extends circumferentially about a circumference of the bleed case, the manifold communicating with and allowing circumferential flow between each one of the bleed ports, wherein the manifold is disposed radially outward of the ligaments, and wherein the manifold is constructed such that the manifold is disposed radially inward of the bleed valve when the bleed valve is in a closed position.

3. The air bleed system of claim 2 , wherein the bleed ports are circumferentially disposed around the bleed case.

4. The air bleed system of claim 2 , wherein the gas turbine engine comprises a turbofan engine.

5. The air bleed system of claim 2 , wherein the gas turbine engine comprises an industrial gas turbine engine.

6. An air bleed system for a gas turbine engine, comprising:

an annular bleed case having a forward section and an aft section and ligaments spanning a gap disposed between an inner surface of the forward section and an inner surface of the aft section whereby each ligament is attached to both the inner surface of the forward section and the inner surface of the aft section such that the ligaments connect the forward section and the aft section; the inner surface of the forward section, the inner surface of the aft section and the ligaments defining a series of bleed ports circumferentially disposed around a circumference of the annular bleed case;

a bleed valve mounted to the annular bleed case; and

a manifold formed between the inner surface of the forward section, the inner surface of the aft section and an outer radial surface of the ligaments, the manifold disposed radially outward of the ligaments and extending circumferentially to communicate with and allow circumferential flow between each one of the series of bleed ports, and wherein the manifold is constructed such that the manifold is disposed radially inward of the bleed valve when the bleed valve is in a closed position.

7. The air bleed system of claim 6 , wherein the gas turbine engine comprises a turbofan engine.

8. The air bleed system of claim 6 , wherein the gas turbine engine comprises an industrial gas turbine engine.