Session: 32-14 ORC & Supersonic Turbines 2

Paper Number: 125893

125893 - Supersonic Convergent-Divergent Vaned Nozzles Design Algorithm and Respective Discharge Coefficient Model 

To continue the series of already published articles on supersonic drilled nozzles [GT2022-83387, GT2023-101760], this publication is devoted to another type of supersonic nozzles, which are formed by vanes providing an annular row of convergent-divergent supersonic channels.

This type of supersonic vaned nozzles, as well as the drilled nozzles, are used in numerous high-loaded turbine applications: turbopumps for liquid rocket engines, high-pressure ratio ORC turbines, drives for various industrial units, etc., where size, weight, and cost reduction are one of the major design criteria.

Published data on this type of nozzles and turbine stages with them have very limited information on both the design methodology and calculation methods and thus do not allow these data to be systematized and implemented into the turbine design and calculation tool.

With this publication, we begin a series of articles on design methodology and calculation methods for this type of nozzle and supersonic turbines with such type of nozzle channels.

The work carried out in this direction includes all the algorithms and models required for the supersonic vaned nozzles design and calculations:

·         The design algorithm of a highly efficient supersonic vaned nozzle

·         The discharge coefficient model

·         The aerodynamic loss model

·         The flow deviation angle model

In this article, we focus on the design algorithm and discharge coefficient model. With that being said in this article the highly efficient supersonic vaned nozzle design algorithm is described including parameterization of the nozzle channel geometry. A list of geometric parameters that uniquely determines the 3D geometry of the nozzle channel that is used in the design algorithm is discussed. The approaches to building convergent and divergent parts of the supersonic nozzle are elaborated. Besides, the model of the discharge coefficient through the critical section of the nozzle is described in detail. The fundamental principles for supersonic flow as well as the results of CFD calculations used for the development of the design algorithm and discharge coefficient model are discussed. The analysis of specific flow phenomena that take place in a supersonic convergent-divergent channel is performed.

The materials devoted to the supersonic vaned nozzle loss and deviation angle models are planned to be published in future articles.

Presenting Author: Leonid Moroz SoftInWay, Inc.

Presenting Author Biography: Leonid Moroz, Ph.D., is the founder and CEO of SoftInWay, Inc.. Upon graduation from Kharkiv Polytechnic Institute (Ukraine) in 1982, Dr. Moroz held various positions at NPO TURBOATOM before founding SoftInWay to design, analyze, and optimize axial and radial turbines, pumps, and compressors. He possesses over 30 years of engineering experience including the development of turbopumps, gas turbine engines, and the design and modeling of turbines for mechanical drives and nuclear power plants. Under his leadership, the AxSTREAM® platform for design, analysis, and optimization of turbomachinery and related subcomponents and systems was developed and implemented globally by turbomachinery OEM and R&D organizations. He is an expert in the internal aerodynamics/hydrodynamics, and rotor dynamics of rotating machinery, and has successfully led multiple projects focused on the design of turbomachinery for aerospace and ground applications. Dr. Moroz holds master's and Ph.D. degrees from the National Technical University “KhPI” (Kharkiv, Ukraine).

Authors:

Leonid Moroz SoftInWay, Inc.
Maksym Burlaka SoftInWay, Inc.
Borys Frolov SoftInWay Switzerland GmbH
Tetiana Dyzenko SoftInWay Switzerland GmbH