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Combustion models for subsonic two-phase reacting flow in ramjet chamber(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2008年02期
Page:
24-30
Research Field:
研究与设计
Publishing date:

Info

Title:
Combustion models for subsonic two-phase reacting flow in ramjet chamber
Author(s):
Huang RixinlTan Yonghua2
1 Xi'an Aerospace Propulsion Institute,Xi'an 710100,China; 2 Academy of Aerospace Propulsion Technology,Xi'an 710100,China
Keywords:
two-phase reacting flowcombustion chamberfinite rateEDCPDFcombustion model
PACS:
TKl6
DOI:
-
Abstract:
The principle,features and development status of six combustion models are re— viewed.Through a mass of computation experiments by different models.it is found that the main difference between these models in ramjet chamber is the reaction type on which the model based:fast chemistry reaction or finite rate reaction.The simulation results of two typical models(eddy dissipa— tion concept model and Locally chemistry equilibrium model)show that finite rate models are more sophisticated,and fast reaction models may cause early combustion,but are in accord with each other very well once after the flame is held in the chamber.All integer parameters such as chamber static pressure and temperature in nozzle exit of both two models fit the experiment data well.

References:

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Memo:
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Last Update: 1900-01-01