Experiments on stability of liquid propellant rocket motors

Lecourt, Renaud; Foucaud, R.

doi:10.2514/6.1987-1772

Cited by 12 publications

(1 citation statement)

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“…One experimental strategy involves forcing resonance of the chamber acoustic modes by modulating the exhaust nozzle flow using a toothed-wheel. 3 Some notable modern systems using the nozzle modulation excitation technique include the Common Research Combustor (CRC) operated by the French National Center for Scientific Research (CNRS) and the German Aerospace Center (DLR), the multi-injector combustor (MIC) and very high amplitude modulator (VHAM) operated by the French Aerospace Lab (ONERA) and CNRS. Each of these is briefly reviewed in the following paragraphs.…”

Section: Introductionmentioning

confidence: 99%

Acoustic characterisation of a rectangular rocket combustor with liquid oxygen and hydrogen propellants

Hardi

Oschwald

Dally

2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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High frequency combustion instabilities have plagued the development of liquid propellant rocket engines since their invention. Continuing research efforts aim to understand the mechanisms by which the oscillating combustion chamber pressure of self-sustaining combustion instabilities is driven. To this end, a rectangular combustor with acoustic forcing, designated 'BKH', was developed to study flame-acoustic interaction under conditions which are representative of real rocket engines. This article describes the acoustic characterisation of the BKH combustor using high frequency dynamic pressure measurements from the first hot-fire tests using liquid oxygen and ambient temperature or cryogenic hydrogen injectants. Analysis of the resulting high frequency pressure measurements shows excellent agreement with the predicted acoustic properties of the system which were calculated using finite element methods.

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Section: Introductionmentioning

confidence: 99%