|Table of Contents|

Numerical simulation on combustion organization scheme of scramjet at high Mach number(PDF)

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

Issue:
2023年05期
Page:
1-12
Research Field:
目次
Publishing date:

Info

Title:
Numerical simulation on combustion organization scheme of scramjet at high Mach number
Author(s):
LI Jiahang1;  SHI Baolu1; 2;  ZHAO Majie1; 2;  WANG Ningfei1
(1.School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China; 2.Chongqing Innovation Center, Beijing Institute of Technology, Chongqing 401120, China)
Keywords:
high Mach number;  scramjet;  combustion organization;  total pressure loss;  internal flow resistance
PACS:
V231.2
DOI:
-
Abstract:
Aiming at the optimization problem of combustion organization scheme for the scramjet engine under high Mach number conditions(Ma=8, where the Mach number in the combustor is 3.88), a numerical simulation method with three-dimensional steady compressible RANS was used to study the combustion scheme with different injection angles and cavity angles. The results indicat that the combustion at high Mach numbers occurs mainly in the cavity and near-wall area of the combustor, and the combustion reaction becomes more intense with the increase of injection angle. Greater injection angles and smaller cavity angles not only lead to higher mixing efficiency and more efficient combustion, but also increase the total pressure loss due to combustion. Under high Mach number conditions, the engine flow resistance is high, which is 7-8 times of the total thrust, and increasing the injection angle and reducing the cavity angle are beneficial for improving the engine performance. Among them, the positive thrust achieved by using a 135° reverse fuel injection is the highest, and the combustion position is relatively forward, which is conducive to the miniaturization of combustor design size.

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Last Update: 1900-01-01