Siemens Energy, Inc.

Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Yan Yin

Kok-Mun Tham

Jiping Zhang

Ching-Pang Lee

Vincent Paul Laurello

Todd A Ebert

Kevin Michael Light

Abdullatif M Chehab

Weidong Cai

Robert W Sunshine

Damien G Teehan

Chirag B Patel

Patrick M Pilapil

David A Kemp

Joshua D Kovac

Ernie B Campbell

John A Fussner

Bijay K Sultanian

John T Fetherolf, Jr

Ashok Reddy Gitta

A method of modulating a cooling supply in a gas turbine engine includes providing the engine comprising a compressor section and a turbine section and including a cooling flow circuit, the cooling flow circuit supplying a cooling air flow from a compressor cavity in the compressor section to a blade ring cavity in the turbine section, wherein the cooling flow circuit includes a main line with a full capacity valve, measuring a first pressure in the blade ring cavity, measuring a second pressure in the compressor cavity, adjusting, by a control system, the opening of the full capacity valve to control the cooling air flow through the main line in order to maintain a target pressure ratio, wherein the pressure ratio defined as a ratio of the first pressure to the second pressure. The method is performed in an ambient temperature operating range of the engine.

Method for modulating a turbine cooling supply for gas turbine applications

A cooling system configured to cool aspects of the turbine engine between a compressor and a turbine assembly is disclosed. In at least one embodiment, the cooling system may include one or more mid-frame cooling channels extending from an inlet through one or more mid-frame torque discs positioned downstream of the compressor and upstream of the turbine assembly. The inlet may be positioned to receive compressor bleed air. The mid-frame cooling channel may be positioned in a radially outer portion of the mid-frame torque disc to provide cooling to outer aspects of the mid-frame torque disc such that conventional, low cost materials may be used to form the mid-frame torque disc rather than high cost materials with capacity to withstand higher temperatures. The cooling fluid routed through the mid-frame cooling channel in the mid-frame torque disc may be exhausted into a cooling system () for the downstream turbine assembly.

Compressor bleed cooling system for mid-frame torque discs downstream from a compressor assembly in a gas turbine engine

An interstage seal system () for adjusting the position of an interstage seal during operation of a gas turbine engine () to increase efficiency of the seal () is disclosed. The interstage seal system () may include a interstage seal housing () formed from a circumferentially extending housing having a seal () positioned on a radially inward surface () of the interstage seal housing (). The interstage seal housing () may biased radially outward via one or more springs () to bias the radially inward surface () of the interstage seal housing () outwardly. The interstage seal housing () may reside in an interstage housing receiving cavity (). The cavity () may be supplied with gases at a higher pressure than on the other side () of the seal housing () during turbine engine operation. As such, the interstage seal housing () is forced radially inwardly to close the gap () within the seal () as the high pressure force directed radially inward overcomes the spring bias directed radially outward.

Interstage seal housing optimization system in a gas turbine engine

Cooling air is provided from a source of cooling air through a cooling air circuit in a turbine section of a gas turbine engine. A first portion of cooling air is provided from the source along a first path of the circuit to a plurality of blades associated with a stage of the turbine section. A second portion of cooling air is provided from the source along a second path of the circuit. The second path includes a turbine disc bore where the cooling air provides cooling to a radially innermost portion of at least one turbine disc that forms a part of a rotor of the engine. The second path is independent from the first path such that the second portion of cooling air bypasses the stage and is not mixed with the first portion of cooling air in the circuit after leaving the source.

Cooling air configuration in a gas turbine engine

A cooling fluid air injection system for use in a gas turbine engine includes at an external cooling fluid source, at least one rotor cooling pipe, which is used to inject cooling fluid from the source into a rotor chamber, a piping system that provides fluid communication between the source and the rotor cooling pipe(s), a blower system for conveying the cooling fluid through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent cooling fluid from the source from passing through the piping system, and open during less than full load engine operation to allow cooling fluid from the source to pass through the piping system.

External cooling fluid injection system in a gas turbine engine

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Oviedo, FL, United States of America

Yan Yin