US4040767A — Coolable nozzle guide vane

Claim 1

Independent Claim 348 words

In a gas turbine engine having a flow path which extends axially through the turbine section of the engine, a nozzle guide vane disposed across the path, which includes: an airfoil section comprising a pressure wall having an inner surface and a multiplicity of cooling holes disposed therein, a suction wall having an inner surface and a multiplicity of cooling holes disposed therein, and which is joined to the pressure wall forming an airfoil cavity therebetween, a plurality of sealing ribs which extend from the inner surfaces of the pressure and suction walls of the airfoil section in a spanwise direction with respect to the airfoil section, and baffle means within the airfoil cavity which contact the ribs forming a plurality of axially adjacent chambers along the inner surfaces of the platform and suction walls, the baffle means having a multiplicity of orifices which are sized and spaced to provide flow into each chamber from the airfoil cavity at a velocity which is sufficient to cause the admitted air to impinge upon the opposing inner surfaces of the airfoil walls; and a platform section having an internal platform cavity and comprising a pressure wall having an inner surface and a multiplicity of cooling holes disposed therein, a suction wall having an inner surface and a multiplicity of cooling holes disposed therein, a plurality of sealing ribs which extend into the platform cavity from the inner surfaces of the pressure and suction walls of the platform section, and baffle means within the platform cavity which contact the ribs forming a plurality of adjacent chambers, the baffle means having a multiplicity of orifices which are sized and spaced to provide flow into each chamber from the platform cavity at a velocity which is sufficient to cause the admitted air to impinge upon the inner surfaces of the platform walls, the cooling holes of said platform and airfoil walls and the orifices of said airfoil and platform baffle means being sized and spaced to provide a diminished cooling air pressure in each axially adjacent downstream chamber during operation of the engine.

Claim 2

Dependent Claim 348 words

In a gas turbine engine having a flow path which extends axially through the turbine section of the engine, a nozzle guide vane disposed across the path, which includes: an airfoil section comprising a pressure wall having an inner surface and a multiplicity of cooling holes disposed therein, a suction wall having an inner surface and a multiplicity of cooling holes disposed therein, and which is joined to the pressure wall forming an airfoil cavity therebetween, a plurality of sealing ribs which extend from the inner surfaces of the pressure and suction walls of the airfoil section in a spanwise direction with respect to the airfoil section, and baffle means within the airfoil cavity which contact the ribs forming a plurality of axially adjacent chambers along the inner surfaces of the platform and suction walls, the baffle means having a multiplicity of orifices which are sized and spaced to provide flow into each chamber from the airfoil cavity at a velocity which is sufficient to cause the admitted air to impinge upon the opposing inner surfaces of the airfoil walls; and a platform section having an internal platform cavity and comprising a pressure wall having an inner surface and a multiplicity of cooling holes disposed therein, a suction wall having an inner surface and a multiplicity of cooling holes disposed therein, a plurality of sealing ribs which extend into the platform cavity from the inner surfaces of the pressure and suction walls of the platform section, and baffle means within the platform cavity which contact the ribs forming a plurality of adjacent chambers, the baffle means having a multiplicity of orifices which are sized and spaced to provide flow into each chamber from the platform cavity at a velocity which is sufficient to cause the admitted air to impinge upon the inner surfaces of the platform walls, the cooling holes of said platform and airfoil walls and the orifices of said airfoil and platform baffle means being sized and spaced to provide a diminished cooling air pressure in each axially adjacent downstream chamber during operation of the engine.

Claim 3

Dependent Claim 59 words

The invention according to claim 1 further including within the platform section a pressure chamber and a circumferentially adjacent suction chamber and wherein the cooling holes of the platform walls and the orifices of the platform baffle means are sized and spaced to provide a higher cooling air pressure in each pressure chamber than in the adjacent suction chamber.

Claim 4

Dependent Claim 345 words

In a turbine section of a gas turbine engine having a flow path for working medium gases and including a nozzle guide vane having an airfoil section including a pressure wall and a suction wall which is disposed across the flow path, and having a platform section including a pressure wall and a suction wall which form a portion of an outer shroud radially enclosing the flow path, the improvement which comprises: a platform cavity which is located radially outward from the pressure and suction walls of the platform section and is adapted to receive cooling air for subsequent distribution about the nozzle guide vane; an airfoil cavity which is located between the suction and pressure walls of the airfoil section and which is in gas communication with the platform cavity; a plurality of axially adjacent platform chambers which are formed between the walls of the platform section and a platform baffle which is spaced apart therefrom, wherein the baffle has a plurality of orifices which are sized and spaced to provide flow into each chamber from the platform cavity at a velocity which is sufficient to cause the admitted air to impinge upon the opposing inner surfaces of the walls and wherein the walls contain a multiplicity of cooling holes which are sized and spaced to flow cooling air therethrough at velocities which will enable the exuding air to adhere to the outer surface of the wall; and a plurality of axially adjacent airfoil chambers which are formed between the walls of the airfoil section and an airfoil baffle which is spaced apart therefrom, wherein the baffle has a plurality of orifices which are sized and spaced to provide flow into each chamber from the airfoil cavity at a velocity which is sufficient to cause the air to impinge upon the opposing inner surfaces of the walls and wherein the walls contain a multiplicity of cooling holes which are sized and spaced to flow cooling air therethrough at velocities which will enable the exuding flow to adhere to the outer surfaces of the wall.

Claim 5

Dependent Claim 345 words

In a turbine section of a gas turbine engine having a flow path for working medium gases and including a nozzle guide vane having an airfoil section including a pressure wall and a suction wall which is disposed across the flow path, and having a platform section including a pressure wall and a suction wall which form a portion of an outer shroud radially enclosing the flow path, the improvement which comprises: a platform cavity which is located radially outward from the pressure and suction walls of the platform section and is adapted to receive cooling air for subsequent distribution about the nozzle guide vane; an airfoil cavity which is located between the suction and pressure walls of the airfoil section and which is in gas communication with the platform cavity; a plurality of axially adjacent platform chambers which are formed between the walls of the platform section and a platform baffle which is spaced apart therefrom, wherein the baffle has a plurality of orifices which are sized and spaced to provide flow into each chamber from the platform cavity at a velocity which is sufficient to cause the admitted air to impinge upon the opposing inner surfaces of the walls and wherein the walls contain a multiplicity of cooling holes which are sized and spaced to flow cooling air therethrough at velocities which will enable the exuding air to adhere to the outer surface of the wall; and a plurality of axially adjacent airfoil chambers which are formed between the walls of the airfoil section and an airfoil baffle which is spaced apart therefrom, wherein the baffle has a plurality of orifices which are sized and spaced to provide flow into each chamber from the airfoil cavity at a velocity which is sufficient to cause the air to impinge upon the opposing inner surfaces of the walls and wherein the walls contain a multiplicity of cooling holes which are sized and spaced to flow cooling air therethrough at velocities which will enable the exuding flow to adhere to the outer surfaces of the wall.

Claim 6

Dependent Claim 111 words

The invention according to claim 3 which further includes a plurality of circumferentially adjacent platform chambers which are formed between the walls of the platform section and a platform baffle which is spaced apart therefrom, wherein the baffle has a plurality of orifices which are sized and spaced to provide flow into each chamber at a velocity which is sufficient to cause the air to impinge upon the opposing inner surfaces of the walls and wherein the walls contain a multiplicity of cooling holes which are sized and spaced to flow cooling air therethrough at velocities which will enable the exuding flow to adhere to the outer surfaces of the walls.

Claim 7

Dependent Claim 33 words

The invention according to claim 4 which further includes means comprising baffle orifices and wall holes for maintaining during operation a greater pressure in each upstream chamber than in the adjacent downstream chamber.

Claim 8

Dependent Claim 51 words

The invention according to claim 5 wherein the circumferentially adjacent platform chambers comprise alternating suction wall and pressure wall chambers and which further includes means including baffle orifices and wall holes for maintaining during operation a greater pressure in each pressure wall chamber than in the circumferentially adjacent suction wall chamber.

Claim 9

Dependent Claim 13 words

The invention according to claim 3 wherein the nozzle guide vane is rotatable.

Claim 10

Dependent Claim 42 words

The invention according to claim 3 wherein said baffle orifices and said wall holes are sized and spaced so as to establish a pressure ratio across the platform and airfoil baffles which is within the range of 1.1 to 1.85 during operation.

Claim 11

Dependent Claim 40 words

The invention according to claim 3 wherein said baffle orifices and said wall holes are sized and spaced so as to establish a pressure ratio across the walls of the platform and airfoil sections which is approximately 1.25 during operation.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1980-08-08	1981-02-07	1981-08-09	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	1984-08-08	1985-02-07	1985-08-09	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	1988-08-08	1989-02-07	1989-08-09	$7700.00	Window Closed / Lapsed

Coolable nozzle guide vane

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