US 6,185,925 B1 · External cooling system for turbine frame

Abstract

An apparatus for cooling a gas turbine engine annular rear turbine frame includes a first plenum box having an inlet for receiving cooling air and an annular first manifold tube in fluid communication with a first outlet of and extending in a first circumferential direction away from the plenum box. The first manifold tube is circumscribed radially outward of and around a centerline and has axially spaced apart first arcuate sections circumscribed about and perpendicular to the centerline. Each of the first arcuate sections of the first manifold tube has a corresponding portion of a first plurality of impingement cooling holes disposed through the first manifold tube and aimed generally radially inward. In one embodiment the impingement cooling holes are aimed towards a first circumference on the frame and A cooling air bleed is preferably connected to the plenum box with a selectable on and off control valve therebetween.

Claims20

Dependent claims

An apparatus for cooling a gas turbine engine annular turbine frame, said apparatus comprising:

an annular first manifold tube in fluid communication with a source of cooling air,
said first manifold tube circumscribed radially outward of and around a centerline,
said first manifold tube having axially spaced apart first arcuate sections circumscribed about and perpendicular to said centerline, and
each of said first arcuate sections of said first manifold tube having a corresponding portion of a first plurality of impingement cooling holes disposed through said first manifold tube and aimed generally radially inward.

1 more element

A cooling system for a gas turbine engine, said apparatus comprising:

an annular turbine frame having annular structural radially outer and inner rings respectively fixedly connected by a plurality of circumferentially spaced apart struts,
said outer ring including an annular casing,
a cooling apparatus for cooling said frame, said cooling apparatus comprising;
a first plenum box having an inlet for receiving cooling air,
axially spaced apart annular forward and aft manifold tubes in fluid communication with first and second outlets respectively of said plenum box,
said forward and aft manifold tubes extending in opposite first and second circumferential directions respectively away from said plenum box,
said forward and aft manifold tubes circumscribed radially outward of and around a centerline,
said forward and aft manifold tubes having forward and aft axially spaced apart arcuate sections circumscribed about and perpendicular to said centerline, and
each of said arcuate sections of said forward and aft manifold tubes having corresponding forward and aft portions of forward and aft pluralities of impingement cooling holes disposed through said forward and aft manifold tubes and aimed generally radially inward.

6 more elements

A cooling system for a gas turbine engine, said apparatus comprising:

an annular turbine frame having annular structural radially outer and inner rings respectively fixedly connected by a plurality of circumferentially spaced apart struts,
said outer ring including an annular casing disposed between forward and aft flanges,
a cooling apparatus for cooling said frame, said cooling apparatus comprising;
a first plenum box having an inlet for receiving cooling air,
an annular forward manifold tube spaced axially apart from and forward of an annular aft manifold tube in fluid communication with first and forward and aft outlets respectively of said plenum box,
said forward and aft annular manifold tubes extending in opposite first and second circumferential directions respectively away from said plenum box,
a counter flow means to flow cooling air in said first and second manifold tubes in opposite first and second circumferential directions respectively,
said counter flow means comprising said first and second outlets being circumferentially spaced apart in circumferentially opposite sides of said plenum box,
said forward and aft manifold tubes circumscribed radially outward of and around a centerline,
said forward manifold tube having three forward axially spaced apart arcuate sections circumscribed about and perpendicular to said centerline,
said aft manifold tube each having three aft axially spaced apart arcuate sections circumscribed about and perpendicular to said centerline,
said forward arcuate sections having three corresponding forward portions of forward pluralities of impingement cooling holes disposed through said forward manifold tube and aimed generally radially inward,
said aft arcuate sections having three corresponding aft portions of aft pluralities of impingement cooling holes disposed through said aft manifold tube and aimed generally radially inward,
said three forward portions of forward pluralities of impingement cooling holes are circumferentially disposed along corresponding axially spaced apart first, second, and third forward arcs on said each of said forward arcuate sections and aimed at first, second, and third forward circles respectively on said casing circumscribed about said centerline,
said three aft portions of aft pluralities of impingement cooling holes are circumferentially disposed along corresponding axially spaced apart first, second, and third aft arcs on said each of said aft arcuate sections and aimed at first, second, and third forward circles respectively wherein said first and second forward circles are on said casing circumscribed about said centerline and said third forward circles is on a nozzle cowl attached to said aft flange, and
clevises for mounting the engine, said clevises mounted on said annular casing, and at least a first one of said three forward portions of forward pluralities of impingement cooling holes in at least one of said forward arcs on said forward arcuate sections are aimed at aimed to impinge on said clevises.

13 more elements

Dependencies are inferred from the claim text.

External cooling system for turbine frame

Life of this patent

External cooling system for turbine frame

Life of this patent

Abstract

Claims20