Combination compressor casing-air manifold structure

Claim 2

In a gas turbine engine comprising a compressor section, a combustor section, and a turbine section downstream of the combustor section, a combination compressor casing-bleed air plenum structure which comprises: a primary compressor casing which includes a forward section immediately surrounding the compressor rotor and adapted to support on its interior surface a plurality of stages of stator blades, and a concentric rearward section whose wall is radially spaced from said rotor; an inner compressor casing immediately surrounding at least one aft stage of the compressor rotor and telescoped within the rearward portion of said primary compressor casing; means supporting said inner compressor casing in the stated telescoped relationship so that its forward end is axially spaced from the forward section of said primary compressor casing, whereby the forward end of said inner compressor casing in cooperation with an interior surface of said primary compressor casing defines a peripheral orifice for bleeding high-pressure air from a compressor stage, and further wherein said inner compressor casing and the rearward portion of said primary compressor casing cooperate to from a bleed air manifold in the compressor section of said engine; a peripheral rib near the forward end of said inner compressor casing and spaced therefrom, said rib radially extending to a position adjacent the interior of said rearward section and including a plurality of axially oriented passages therethrough, thereby dividing said bleed air manifold into two compartments, whereby said forward compartment acts as an accumulator to attenuate perturbations in the removal of air from said rear compartment, thereby minimizing flow disturbances in the compressor; and means for extracting air from said plenum included in the rear compartment.

Claim 3

The structure recited in claim 1 wherein the forward end of said inner compressor casing includes a narrow lip which in cooperation with an adjacent interior surface of said primary compressor casing defines an uninterrupted peRipheral interstage bleed orifice.

Claim 4

The structure recited in claim 2 wherein said lip is directed generally radially toward the said adjacent interior surface to define therewith an annular orifice.

Claim 5

The structure recited in claim 1 wherein said inner compressor casing comprises at least two cylindrical sectors, each of which includes axial bolting flanges radially extending from their exterior surfaces, said sectors being joined together at said flanges, and further wherein said structure includes means for providing airflow communication between the sectors of said bleed air manifold defined by the said flanges.

Claim 6

In a gas turbine engine comprising a compressor section, a combustor section downstream thereof, and a turbine section downstream of the combustor section, a combination casing -bleed air plenum structure which comprises: a primary compressor casing which includes a forward section immediately surrounding the compressor rotor and adapted to support on its interior surface a plurality of stages of stator blades, and a concentric rearward section whose wall is radially spaced from said rotor, said rearward section including at its aft end a peripheral bolting flange normal to the axis thereof; a second structural member which comprises an outer shell which includes at its forward end a peripheral flange secured to said first-mentioned flange, an inner wall concentric with said outer shell, and an end wall connecting said outer shell and said inner wall at a location removed from said latter mentioned flange, said inner wall extending from said end wall to a plane approximate that of said flanges, said outer shell, inner wall, and end wall defining a uninterrupted annulus in said second structural member; and an inner compressor casing supported by said inner wall and telescoped within the rearward portion of said primary compressor casing and maintained with its forward edge in spaced relation with the forward section of said primary compressor casing, said inner compressor casing comprising an annular wall member and means on the interior thereof for supporting at least one stage of stator blades; said inner compressor casing and said inner wall cooperating to from one wall of an air plenum chamber and the rearward portion of said primary compressor casing cooperating with said outer shell to form an outer plenum wall concentric with said one wall; said structure further including bleed means for the passage of air from the interior of said casing to said plenum, said bleed means comprising a peripheral lip extending radially from the forward end of said inner compressor casing to radially spaced relation with the interior surface of the rearward portion of said primary compressor casing, thereby defining an annular bleed orifice.

Claim 7

In a gas turbine engine comprising a compressor section, a combustor section downstream thereof, and a turbine section downstream of the combustor section, a combination casing -bleed air plenum structure which comprises: a primary compressor casing which includes a forward section immediately surrounding the compressor rotor and adapted to support on its interior surface a plurality of stages of stator blades, and a concentric rearward section whose wall is radially spaced from said rotor, said rearward section including at its aft end a peripheral bolting flange normal to the axis thereof; a second structural member which comprises an outer shell which includes at its forward end a peripheral flange secured to said first-mentioned flange, an inner wall concentric with said outer shell, and an end wall connecting said outer shell and said inner wall at a location removed from said latter mentioned flange, said inner wall extending from said end wall to a plane approximate that of said flanges, said outer shell, inner wall, and end wall defining a uninterrupted annulus in said second structural member; and an inner compressor casing supported by said inner wall and telescoped within the rearward portion of said primary compressor casing and maintained with its forward edge in spaced relation with the forward section of said primary compressor casing, said inner compressor casing comprising an annular wall member and means on the interior thereof for supporting at least one stage of stator blades; said inner compressor casing and said inner wall cooperating to from one wall of an air plenum chamber and the rearward portion of said primary compressor casing cooperating with said outer shell to form an outer plenum wall concentric with said one wall; said structure further including bleed means for the passage of air from the interior of said casing to said plenum, said bleed means comprising a peripheral lip extending radially from the forward end of said inner compressor casing to radially spaced relation with the interior surface of the rearward portion of said primary compressor casing, thereby defining an annular bleed orifice.

Claim 8

The structure recited in claim 5 wherein said inner compressor casing further includes a peripheral rib near its forward end and spaced therefrom, said rib radially extending to be adjacent the interior of said rearward section and including a plurality of axially oriented passages therethrough, thereby dividing said plenum into two compartments, the forward compartment defined by said peripheral lip and said rib and the rearward compartment defined by said rib and said end wall. whereby said forward compartment acts as an accumulator to attenuate perturbations in the removal of air from said rear compartment, thereby minimizing flow disturbances in the compressor.