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RESEARCH PAPERS

Compound-Compressible Nozzle Flow

[+] Author and Article Information
A. Bernstein, C. Hevenor

Pratt & Whitney Aircraft, East Hartford, Conn.

W. H. Heiser

Department of Mechanical Engineering, Massachusetts Institute of Technology, Cambridge, Mass.

J. Appl. Mech 34(3), 548-554 (Sep 01, 1967) (7 pages) doi:10.1115/1.3607742 History: Received November 15, 1966; Online September 14, 2011

Abstract

A one-dimensional theory based upon fundamental flow relationships is presented for analyzing the behavior of one or more gas streams flowing through a single nozzle. This compound-compressible flow theory shows that the behavior of each stream is influenced by the presence of the other streams. The theory also shows that the behavior of compound-compressible flow is predicted by determining how changing conditions at the nozzle exit plane affect conditions within the nozzle. It is found that, when choking of the compound-compressible flow nozzle occurs, an interesting phenomenon exists: The compound-compressible flow is shown to be choked at the nozzle throat, although the individual stream Mach numbers there are not equal to one. This phenomenon is verified by a wave analysis which shows that, when choking occurs, a pressure wave cannot be propagated upstream to the nozzle throat even though some of the individual streams have Mach numbers less than one. Algebraic methods based on this compound-compressible flow theory are used to demonstrate the usefulness of this approach in computing the behavior of compound-compressible flow nozzles. A comparison of the compound-compressible flow theory with three-dimensional computer calculations shows that the effects of streamline curvature on nozzle behavior can be disregarded for many practical nozzle configurations. Test results from a typical two-flow nozzle show excellent agreement with the predictions from the theory.

Copyright © 1967 by ASME
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