Aerodynamic seal for a rotary machine

Claim 2

Within a cavity formed between the rotating and stationary elements of a rotary machine, apparatus for decreasing the radial mass flow rate through the air boundary layer which is adjacent to the rotating element wherein said apparatus includes air swirl means for accelerating air within the cavity to a tangential velocity which approximates the tangential velocity of the rotating element at a corresponding radial position.

Claim 3

The invention according to claim 1 wherein said air swirl means comprises a pluraity of nozzles disposed circumferentially about the cavity and adapted so as to discharge air flowing therethrough during operation of the engine in a substantially tangential direction.

Claim 4

The invention according to claim 2 wherein said nozzles extend from the stationary element.

Claim 5

A rotary machine structure comprising a stationary element having a diaphragm which extends in an essentially radial direction and a rotating element having a side surface which is spaced apart from said diaphragm to form a cavity therebetween, and including, disposed across the radially outward end of the cavity means for swirling the air within the outward portion of the cavity at a tangential velocity which approximates the tangential velocity of the rotating element to impose upon the air within the air boundary layer, which is adjacent the rotating element, a radial pressure gradient which is equal in magnitude and opposite in direction to the radial acceleration of the air within the boundary layer.

Claim 6

A rotary machine structure comprising a stationary element having a diaphragm which extends in an essentially radial direction and a rotating element having a side surface which is spaced apart from said diaphragm to form a cavity therebetween, and including, disposed across the radially outward end of the cavity means for swirling the air within the outward portion of the cavity at a tangential velocity which approximates the tangential velocity of the rotating element to impose upon the air within the air boundary layer, which is adjacent the rotating element, a radial pressure gradient which is equal in magnitude and opposite in direction to the radial acceleration of the air within the boundary layer.

Claim 7

The invention according to claim 4 wherein said swirling means is a plurality of circumferentially disposed air injection nozzles.

Claim 8

Apparatus for preventing the radially inward ingestion of working medium gases from the flow path of a gas turbine engine into an internal cavity between the rotating and stationary elements of the machine, comprising: a plurality of a nozzle circumferentially disposed at the radially outward end of the cavity and so oriented as to cause the air flowing therefrom during operation of the engine to accelerate the air within the outward portion of the cavity to a tangential velocity which is substantially equal to the tangential velocity of the rotating element at a corresponding radial position.

Claim 9

Apparatus for preventing the radially inward ingestion of working medium gases from the flow path of a gas turbine engine into an internal cavity between the rotating and stationary elements of the machine, comprising: a plurality of a nozzle circumferentially disposed at the radially outward end of the cavity and so oriented as to cause the air flowing therefrom during operation of the engine to accelerate the air within the outward portion of the cavity to a tangential velocity which is substantially equal to the tangential velocity of the rotating element at a corresponding radial position.

Claim 10

In the gas turbine engine of the type having a cavity located radially inward of the flow path of the working medium gases between the rotating and stationary elements of the engine, a method for preventing the ingestion of working medium gases from the flow path into the cavity, comprising: flowing air tangentially into the radially outer end of the cavity so as to accelerate the air within the cavity to a tangential velocity which is substantially equal to the tangential velocity of the rotor at a corresponding radial location.

Claim 11

In the gas turbine engine of the type having a cavity located radially inward of the flow path of the working medium gases between the rotating and stationary elements of the engine, a method for preventing the ingestion of working medium gases from the flow path into the cavity, comprising: flowing air tangentially into the radially outer end of the cavity so as to accelerate the air within the cavity to a tangential velocity which is substantially equal to the tangential velocity of the rotor at a corresponding radial location.