General Electric Company

Robert J Meade

Richard William Albrecht, Jr

Christopher Charles Glynn

Robert Harold Weisgerber

John T Kutney, Jr

Jeffrey C Martin

Norbert E Meyer

Stephen D Abernathy

An axial retention system for an interstage seal located in a gas turbine engine of a type having a turbine section including a first stage disk and a second stage disk. The interstage seal includes a web portion having an aft arm extending from said web, the aft arm having a peripheral rim adjacent the second stage disk. The axial retention system comprising a split ring having two overlapping ends and a plurality of radially outwardly extending tabs for engaging a plurality of inwardly extending tabs located on the second stage disk adjacent the peripheral rim, in a bayonet connection. The retaining ring is located within a slot formed in the peripheral rim and the outwardly extending tabs are positioned in a passageway formed by the disk tabs.

Turbine disk interstage seal axial retaining ring

An anti-rotation system for an interstage seal located in a gas turbine engine of a type having a turbine section including a first stage disk having a rearwardly extending aft shaft and a second stage disk. The interstage seal includes a rearwardly projecting conical arm mounted on the first stage disk. The interstage seal anti-rotation system includes a key inserted within an opening formed between the aft shaft and the conical arm for preventing circumferential movement between the aft shaft and the conical arm by providing a double shear plane between the aft shaft and the conical arm. A circumferential wire is inserted within a slot formed in the conical arm and a groove on the key for preventing axial movement of the key.

Turbine disk interstage seal anti-rotation system

An anti-rotation system for an interstage seal located in a gas turbine engine of a type having a turbine section including a first stage disk and a second stage disk, each having a plurality of dovetail slots. The interstage seal is located between the disks and includes a web portion having a forward arm and an aft arm, the aft arm having a bayonet connection for preventing relative axial movement between the second stage disk and the seal The interstage seal anti-rotation system includes a key positioned in at least one dovetail slot and having a tab for interconnecting with a slot formed in the aft arm bayonet connection. The key prevents relative circumferential movement between the interstage seal and the second stage disk An aft seal plate is provided for retaining the key in the interconnected position between the seal and the second stage disk. The key is contoured to coincide with the dovetail slot for maximizes the translation of tangential load from the interstage seal to the second stage disk, and includes a slot formed along its length for allowing blade cooling air to flow radially outward to the turbine blades.

Turbine disk interstage seal anti-rotation key through disk dovetail slot

A split ring seal having an outer split ring and an inner split ring with the inner and outer split rings having overlapping portions. The split ring seal is located between a seating seal and a carrier and separates a high pressure cavity from a low pressure cavity. Movement of the split ring seal is restricted by sidewalls of the carrier. A diagonal edge on the outer ring reacts against centrifugal loading from the inner ring so that said outer ring is urged axially against a sidewall of the carrier to form a positive seal for blocking any leakage path between the high and low pressure cavities.

Rotor to rotor split ring seal

A turbine engine of the type having a compressor section, combustor section and high-pressure turbine section in which compressor air is conveyed internally of the compressor and turbine sections to cool the turbine interstage volume, a first stage turbine disk includes a shaft supporting a second stage turbine disk, a turbine interstage seal is secured by boltless engagement to the disks and is prestressed to resist flexure, and the first stage disk carries a forward seal attached by boltless connections. The interstage seal includes a bore having a rearwardly-extending arm engaging the aft shaft in a bayonet connection to prevent deflection of the bore and includes passages to allow air flow around the bore. The forward seal includes radially-extending vanes to convey cooling air along the disk, and is secured by inward and outward bayonet connections, the inward connection including locking pins which are arranged to perform a balancing function.

Turbine disk interstage seal system

A labyrinth seal for a gas turbine engine of the type having a high pressure compressor and high pressure turbine, an outer shaft interconnecting the high pressure compressor and turbine, a low pressure compressor and turbine, and an inner shaft interconnecting the low pressure compressor and turbine in which the shafts are concentric and are separated by the seal. The labyrinth seal includes a cylindrical sleeve which is discrete from and attached to the outer shaft, and which includes a plurality of annular seal teeth extending radially inwardly to the inner shaft. By placing the seal teeth on a sleeve which is discrete from the outer shaft and is easily replaceable, stress cracks created in the region of the seal teeth are prevented from propagating to the outer shaft and maintenance of the shafts is facilitated. Further, by configuring the seal teeth to extend, radially inwardly between two relatively rotating components, the fluid trapped by the seal is forced to take a tortuous path along the inner shaft; as a result, the seal of the present invention is more efficient at high temperatures and rotational speeds. The sleeve is captured between an annular rabbet at an aft end and radial slots formed on a seal tube the latter of which engage spaced, axially-extending fingers on the sleeve at the forward end of the sleeve. The sleeve is at a relatively low radius where mechanical deflections due to centrifugal loads of the two concentric shafts are similar. Deflection of the seal teeth is away from the inner shaft due to thermal effects in the concentric shafts.

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West Chester, OH, United States of America

Robert J Meade