SU70727A1 - Apparatus for cooling hollow blades of internal combustion turbines - Google Patents

Description

As is well known, as the gas temperature in the internal combustion turbine rises, its efficiency increases and the size of the installation decreases. The absence of sufficiently heat-resistant materials that can withstand high temperatures raises the question of cooling turbine blades.

A number of devices are known in the art for cooling hollow blades of an internal combustion turbine with liquid flowing through the blades.

The present invention relates to such an arrangement of devices, but differs from them in that a rotating annular grooved receiver open on the gas flow side is used to receive coolant, and an overflow tube is used to limit the minimum clearance between the ends of the blades and the surface of the liquid.

The drawing shows a partial section of a turbine wheel with the proposed device.

The device consists of a rotating annular grooved receiver 7, bounded on three sides by solid walls. The open side of the receiver is facing the flow of gases entering the turbine blades 2. The upper wall of the receiver has openings 3 for the passage of fluid from the cavity of the receiver to the undercut 4 for collecting fluid. To limit the minimum clearance between the ends of the vanes 2 and the surface 5 of the fluid in receiver 7, the latter is provided with an overflow tube 6 through which excess fluid discharged into the annular recess 7. Liquid from the recesses 4 and 7 through the tubes 8 is discharged into the tank (not shown). The grooved receiver 7 can be rotated from any drive, regardless of the movement of the turbine blades 2.

The cooling process of the turbine blades 2 is as follows.

During turbine operation, fluid through the hollow shaft of the turbine (not shown) enters the disk 9, and from it into the hollow blades 2. Under the action of centrifugal force, the liquid flows into the rotating annular grooved receiver 7,

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which the liquid is heated through the holes 3 enters the recess 4, from where it is discharged through the tube S to the tank.

Thus, during the rotation of the turbine wheel, the fluid flows continuously through the cavities of the blades 2, cools them and returns to the tank when heated.

Subject invention

Claims (2)

1. A device for cooling the hollow blades of internal turbines Combustion by means of a fluid flowing through the blades, characterized in that a rotating annular grooved receiver open from the gas flow side is used to receive coolant. 2. The form of the device pop. 1, characterized in that in order to limit the minimum gap between the ends of the blades and the surface of the liquid in the receiver, an overflow tube is used.