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

Justin S. Hardi, Michael Oschwald, Bassam Dally

Research output: Contribution to journalArticlepeer-review

12 Scopus citations


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. © IMechE 2012.
Original languageEnglish (US)
Pages (from-to)436-446
Number of pages11
JournalProceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
Issue number3
StatePublished - Mar 1 2013
Externally publishedYes

Bibliographical note

Generated from Scopus record by KAUST IRTS on 2022-09-12

ASJC Scopus subject areas

  • Mechanical Engineering
  • Aerospace Engineering


Dive into the research topics of 'Acoustic characterisation of a rectangular rocket combustor with liquid oxygen and hydrogen propellants'. Together they form a unique fingerprint.

Cite this