General Electric Company

Srinivasarao Pakkala

David Martin Johnson

Radu Ioan Danescu

Piotr Edward Kobek

Moorthi Subramaniyan

Kunal Upendra Sakekar

Ravi Shankar Venkata Kasibhotla

Jagdish Prasad Tyagi

A system for controlling compressor forward leakage to the compressor flow path in a gas turbine is provided. The system includes a first compressor rotor wheel coupled to an upstream face of a compressor spacer wheel. A second compressor rotor wheel is coupled to a downstream face of the compressor spacer wheel. The compressor spacer wheel includes at least one intake recess defined in the downstream face, at least one discharge recess defined in the upstream face, and at least one axial passage coupling the at least one intake recess in fluid communication with the at least one discharge recess.

Method and system for controlling compressor forward leakage

A system is provided including a turbine exhaust section. The turbine exhaust section includes an exhaust flow path. The turbine exhaust section also includes an outer structure having an outer casing, an outer exhaust wall disposed along the exhaust flow path, and an outer cavity disposed between the outer exhaust wall and the outer casing. The turbine exhaust section further includes an inner structure having an inner exhaust wall disposed along the exhaust flow path, an inner cavity disposed between the inner exhaust wall and an inner casing, and a bearing cavity disposed between the inner casing and a bearing housing. In addition, the turbine exhaust section includes a strut extending between the outer structure and the inner structure. The strut includes a first flow passage configured to flow a fluid from the inner cavity to the outer cavity.

Turbine exhaust section structures with internal flow passages

A gas turbine exhaust frame includes an inner barrel and an outer barrel establishing an annular exhaust gas flow path therebetween. A plurality of airfoils extend radially between the inner barrel and the radially, outer barrel, the plurality of struts arranged in first and second axially-spaced and circumferentially-staggered rows.

Staggered double row, slotted airfoil design for gas turbine exhaust frame

A system is provided with a turbine exhaust strut configured to provide a bi-directional airflow. The turbine exhaust strut includes a first portion having a first flow passage configured to flow a fluid in a first direction between inner and outer exhaust walls of a turbine exhaust section, and a second portion having a second flow passage configured to flow the fluid in a second direction between the inner and outer exhaust walls of the turbine exhaust section. Furthermore, the first and second directions are opposite from one another.

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West Godavari, India

Srinivasarao Pakkala