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Refinement of Last-Stage Rows of Gas Turbines to Minimize Number and Size of Separated Zones on Diffuser Surfaces

Gas turbine diffusers can be categorized into two types. The first type is an annular diffuser with a central body that extends from the beginning of the diffuser to its end. Provided the length of such a diffuser, usually two rows of power-supply racks are located in it: one near the last rotor bla...

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Bibliographic Details
Published in:Power technology and engineering 2024, Vol.57 (6), p.912-917
Main Authors: Granovskiy, A. V., Afanasiev, I. V., Bekreneva, L. I.
Format: Article
Language:English
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Summary:Gas turbine diffusers can be categorized into two types. The first type is an annular diffuser with a central body that extends from the beginning of the diffuser to its end. Provided the length of such a diffuser, usually two rows of power-supply racks are located in it: one near the last rotor blade of the turbine, and the other near the diffuser outlet. Power-supply racks result in additional losses in the diffuser. Hence, another type of diffuser is often used, which comprises two parts: behind the last stage of the turbine, an annular diffuser with power-supply racks and a central body is used; behind the central body, a conical diffuser begins and extends up to the outlet. The nature of flow behind the central body depends on shape of the outlet part of the central body of the diffuser. Either the flow suddenly expands after the end shape of the outlet part of the central body, or it smoothly decelerates along the pointed outlet part of the diffuser’s central body. Using such a diffuser, the number of rows of racks decreases, but a bottom area appears behind the central body, which can adversely affect the process of flow inhibition in the diffuser. This study examines the influence on the flow structure features and on the characteristics of the diffuser part consisting of an annular diffuser with one row of power-supply racks and a central body, and the distribution of flow parameters behind the last stage of the turbine.
ISSN:1570-145X
1570-1468
DOI:10.1007/s10749-024-01757-3