Siemens Aktiengesellschaft

Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Adam C Pela

Ching-Pang Lee

Mrinal Munshi

Matthew H Lang

Paul Bradley Davis

David James Wiebe

Krishna Chaitanya Veluru

Kenneth W Giersdorf

Krishna C Veluru

A locking spacer assembly for filling a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly in an industrial gas turbine engine is presented. The locking spacer assembly includes a first side piece, a second side piece, a mid piece and a bolt. The bolt is disposed into the mid piece to position the mid piece in a radial position in an assembled state. The mid piece contacts the first side piece and the second side piece in the assembled state to prevent axial movements of the first and second side pieces in the disk groove. The bolt prevents a radial movement of the mid piece.

Locking spacer assembly, corresponding blade assembly, method for installing a locking spacer

A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion for providing structural support for a row of vanes in the engine section, an aft hook, a forward wall, and a strong back plate. The aft hook extends from an aft side of the main body portion and is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The forward wall extends generally radially outwardly from a forward side of the main body portion. The strong back plate spans between the forward wall and the aft hook and effects a reduction in dynamic displacement between the forward wall and the aft hook during operation of the engine.

Outer vane support ring including a strong back plate in a compressor section of a gas turbine engine

A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion to which a row of vanes is affixed for providing structural support for the vanes in the engine section, and an aft hook extending from an aft side of the main body portion with reference to a direction of air flow through the engine section. The aft hook is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The support ring does not include a forward hook having a flange that extends axially from a forward or aft side of the forward hook with reference to the direction of air flow through the engine section.

Vane outer support ring with no forward hook in a compressor section of a gas turbine engine

A wear prevention system for securing compressor airfoils within a turbine engine while reducing wear of related components may include a compressor diaphragm spring positioned in an airfoil receiving channel between a radially outer surface of a diaphragm base and a radially inner surface of the airfoil receiving channel. The spring may bias the diaphragm base and airfoil attached thereto radially inward against upstream and downstream arms formed from upstream and downstream recesses extending axially from the airfoil receiving channel in the compressor case. The compressor diaphragm spring may dampen vibration and increase service life of the diaphragm base.

Wear prevention system for securing compressor airfoils within a turbine engine

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Jupiter, FL, United States of America

Adam C Pela