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Exhaust diffuser for turbine

a technology of exhaust gas and diffuser, which is applied in the direction of machines/engines, stators, liquid fuel engines, etc., can solve the problems of destroying the ability of the diffuser to raise the static pressure, and the design of fully effective diffusers is almost impossibl

Inactive Publication Date: 2013-09-19
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent is about an exhaust diffuser for a turbine that helps to guide and diffuse the exhaust gas. The diffuser has a curved surface that is angled with respect to the turbine's axis and the length of the last stage bucket. By using this design, the exhaust gas flows smoothly through the diffuser and is released at the proper pressure and temperature. This results in a more efficient turbine and better performance.

Problems solved by technology

Unfortunately, the complicated flow patterns existing in such turbines as well as the design problems caused by space limitations make fully effective diffusers almost impossible to design.
A frequent result is flow separation that fully or partially destroys the ability of the diffuser to raise the static pressure as the steam velocity is reduced by increasing the flow area.

Method used

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Examples

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Embodiment Construction

[0013]Referring to FIG. 1, a first exhaust flow diffuser 2 of a steam turbine low pressure section includes an inlet 18 that receives steam passing a last stage bucket 14 of the turbine. The exhaust flow diffuser 2 further includes a steam guide surface 4 that guides the steam flow passing from the last stage bucket 14, and a diffuser end wall 6. A ratio of the axial length L of the diffuser (as measured from a centerline 16 of the last stage bucket 14 to the diffuser end wall 6) to the active length AL of the last stage bucket 14 is approximately 2.0. The centerline 16 of the last stage bucket 14 is a radial line passing through the center of gravity of the bucket's root section.

[0014]Referring still to FIG. 1, a diffuser 8 of a second, different configuration from the diffuser 2 is also shown. The diffuser 8 has a ratio of axial length L (as measured from the centerline 16 to the diffuser end wall 12) to active length AL of the last stage bucket 14 of approximately 1.35. As shown ...

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Abstract

An exhaust diffuser for a turbine includes an inlet configured to receive exhaust gas from a last stage bucket of the turbine and an exhaust gas guide surface configured to guide the exhaust gas. A curvature of the guide surface comprises a first angle with respect to an axis of the turbine and a ratio of a guide surface axial length to the active length of the last stage bucket which is between about 0.45 to 0.70. A method of diffusing exhaust of a turbine includes energizing a boundary layer along a curved exhaust flow guide surface of an exhaust diffuser with over tip leakage of a last stage bucket of the turbine.

Description

[0001]The present invention relates to an exhaust diffuser for a turbine and to methods for reducing flow separation with over tip leakage flow with shrouded and unshrouded last stage buckets of the turbine.BACKGROUND OF THE INVENTION[0002]In the discharge of exhaust steam from an axial flow turbine, for example discharge of this exhaust steam to a condenser, it is desirable to provide as smooth a flow of steam as possible and to minimize energy losses from accumulation of vortices, turbulences and non-uniformity in such flow. Usually the exhaust from the turbine is directed into an exhaust hood and from there through a discharge opening in the hood in a direction essentially normal to the axis of the turbine into a condenser. It is desirable to achieve a smooth transition from axial flow at the exhaust of the turbine to radial flow in the exhaust hood and thence a smooth flow at the discharge opening of this hood into the condenser.[0003]In the constructing of an effective exhaust ...

Claims

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Application Information

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IPC IPC(8): F01D1/00F01D25/00
CPCF01D5/143F01D5/225F01D9/02F01D25/30
Inventor DALSANIA, PRAKASH BAVANJIBHAICOTRONEO, JOSEPH ANTHONYNEELI, SUDHAKAR
Owner GENERAL ELECTRIC CO