Accession Number:

AD1071152

Title:

Influence of Sizing on Rotation Detonation Combustor Performance

Descriptive Note:

Technical Report,30 Sep 2016,29 Sep 2018

Corporate Author:

INSTYTUT LOTNICTWA Warszawa, Poland

Personal Author(s):

Report Date:

2019-01-29

Pagination or Media Count:

34.0

Abstract:

The main goal of the project was to build and start-up a rocket engine with detonation combustion chamber, as well as to create a test stand for testing the engine and detonation. Recently, intensive research on the applications of the continuously rotating detonation CRD in the propulsion system have been undertaken. It has been demonstrated that it is possible to improve the engine efficiency by 3-7 . The simplest engine utilizing a continuously rotating detonation is the rocket engine. In Rotating Detonation Rocket Engines RDRE, the fuel and the oxidizer are injected into a cylindrical detonation chamber, and the rotating detonation continuously propagates as long as the fuel and oxidizer are supplied to the chamber. As a first step the tests were carried out in the shock tube detonation shock tube in order to develop the detonation shock measurement methodology and also as a way for protection of piezoelectric pressure sensors protection against the effects of high temperatures. The research of detonation engine on this stage of project was used to check the influence of combustion chamber geometry primarily the height of combustion chamber on engine performance and detonation parameters. The comparative experiments of rocket engine with detonation combustion chamber and deflagration combustion chamber were conducted. A key result was that an introduced channel eccentricity resulted in 100 receptivity of direction of wave propagations. As well, the number of waves depends directly on critical length of detonation cell lc and rate of mixture supply.

Subject Categories:

  • Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE