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2015•TsAGI science journalRequires access

THERMODYNAMIC ANALYSIS OF DUAL-MODE SCRAMJET COMBUSTOR OPERATION

E. A. Meshcheryakov, Violetta Vasilievna Yashina

Open publisher page 1 citations

Abstract

Thermodynamic analysis of critical regimes (regimes with thermal flow chocking phenomena at the exit) of dual-mode scramjet combustor operation has been performed using a quasi-one-dimensional flow scheme on an example of a heat supply to the gas flow in a duct with supersonic velocity at the entrance. The advantages of combustor subsonic mode of operation have been demonstrated for parameters such as the relative heat supply to the working gas, the total pressure loss in the flow path, and combustor thrust performance. Moreover, using the maximum entropy production principle, the priority (uniqueness) of the subsonic mode of combustor operation under a wide range of scramjet flight Mach numbers (MH = 3−7.5) has been established.

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What this paper is about

Thermodynamic analysis of critical regimes (regimes with thermal flow chocking phenomena at the exit) of dual-mode scramjet combustor operation has been performed using a quasi-one-dimensional flow scheme on an example of a heat supply to the gas flow in a duct with supersonic velocity at the entrance. The advantages of combustor subsonic mode of operation have been demonstrated for parameters such as the relative heat supply to the working gas, the total pressure loss in the flow path, and combustor thrust performance. Moreover, using the maximum entropy production principle, the priority (uniqueness) of the subsonic mode of combustor operation under a wide range of scramjet flight Mach numbers (MH = 3−7.5) has been established.

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Available abstract

Thermodynamic analysis of critical regimes (regimes with thermal flow chocking phenomena at the exit) of dual-mode scramjet combustor operation has been performed using a quasi-one-dimensional flow scheme on an example of a heat supply to the gas flow in a duct with supersonic velocity at the entrance. The advantages of combustor subsonic mode of operation have been demonstrated for parameters such as the relative heat supply to the working gas, the total pressure loss in the flow path, and combustor thrust performance. Moreover, using the maximum entropy production principle, the priority (uniqueness) of the subsonic mode of combustor operation under a wide range of scramjet flight Mach numbers (MH = 3−7.5) has been established.

Key concepts: Combustor, Scramjet, Supersonic speed, Mach number, Hypersonic speed, Mechanics, Aerospace engineering, Materials science

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