A new design approach of a compact high performance bipropellant liquid rocket engine combustors

H. H. Chiu; T. L. Jiang

A new design approach of a compact high performance bipropellant liquid rocket engine combustors

Research output: Contribution to conference › Paper › peer-review

Abstract

Based on the theory of group conjugate and normal combustion of bipropellants, a design procedure of a minimum length combustor for a prescribed combustion efficiency at fixed propellant flow rates and a constant fuel group combustion dumber is developed. Die optimum Sauter Mean Diameter (SMD) and the corresponding droplet number density that give the minimum burner length are provided to aid in the design of an optimum injector. It is estimated, for example, an approximately 10% reduction in a burner length la achieved when the SMD of oxidizer droplets is increased from 20 μm to 60 μm which is the optimum value for the selected flow rates- the minimum length requirement for the optimum burner is attributed to the rapid axial development of the combustion rate rather than the fast vaporization rate. The present approach can be used for all cryogenic propellants, partially cryogenic or non- cryogenic bipropellant combinations.

Original language	English
Publication status	Published - 1987 Jan 1
Event	AIAA/ASME/SAE/ASEE 23rd Joint Propulsion Conference, 1987 - San Diego, United States Duration: 1987 Jun 29 → 1987 Jul 2

Other

Other	AIAA/ASME/SAE/ASEE 23rd Joint Propulsion Conference, 1987
Country	United States
City	San Diego
Period	87-06-29 → 87-07-02

All Science Journal Classification (ASJC) codes

Mechanical Engineering
Aerospace Engineering
Energy Engineering and Power Technology
Control and Systems Engineering
Electrical and Electronic Engineering

Fingerprint Dive into the research topics of 'A new design approach of a compact high performance bipropellant liquid rocket engine combustors'. Together they form a unique fingerprint.

Cite this

@conference{e39eaeda541d491ab2ca6240ca010ac8,

title = "A new design approach of a compact high performance bipropellant liquid rocket engine combustors",

abstract = "Based on the theory of group conjugate and normal combustion of bipropellants, a design procedure of a minimum length combustor for a prescribed combustion efficiency at fixed propellant flow rates and a constant fuel group combustion dumber is developed. Die optimum Sauter Mean Diameter (SMD) and the corresponding droplet number density that give the minimum burner length are provided to aid in the design of an optimum injector. It is estimated, for example, an approximately 10% reduction in a burner length la achieved when the SMD of oxidizer droplets is increased from 20 μm to 60 μm which is the optimum value for the selected flow rates- the minimum length requirement for the optimum burner is attributed to the rapid axial development of the combustion rate rather than the fast vaporization rate. The present approach can be used for all cryogenic propellants, partially cryogenic or non- cryogenic bipropellant combinations.",

author = "Chiu, {H. H.} and Jiang, {T. L.}",

year = "1987",

month = jan,

day = "1",

language = "English",

note = "AIAA/ASME/SAE/ASEE 23rd Joint Propulsion Conference, 1987 ; Conference date: 29-06-1987 Through 02-07-1987",

}

TY - CONF

T1 - A new design approach of a compact high performance bipropellant liquid rocket engine combustors

AU - Chiu, H. H.

AU - Jiang, T. L.

PY - 1987/1/1

Y1 - 1987/1/1

N2 - Based on the theory of group conjugate and normal combustion of bipropellants, a design procedure of a minimum length combustor for a prescribed combustion efficiency at fixed propellant flow rates and a constant fuel group combustion dumber is developed. Die optimum Sauter Mean Diameter (SMD) and the corresponding droplet number density that give the minimum burner length are provided to aid in the design of an optimum injector. It is estimated, for example, an approximately 10% reduction in a burner length la achieved when the SMD of oxidizer droplets is increased from 20 μm to 60 μm which is the optimum value for the selected flow rates- the minimum length requirement for the optimum burner is attributed to the rapid axial development of the combustion rate rather than the fast vaporization rate. The present approach can be used for all cryogenic propellants, partially cryogenic or non- cryogenic bipropellant combinations.

AB - Based on the theory of group conjugate and normal combustion of bipropellants, a design procedure of a minimum length combustor for a prescribed combustion efficiency at fixed propellant flow rates and a constant fuel group combustion dumber is developed. Die optimum Sauter Mean Diameter (SMD) and the corresponding droplet number density that give the minimum burner length are provided to aid in the design of an optimum injector. It is estimated, for example, an approximately 10% reduction in a burner length la achieved when the SMD of oxidizer droplets is increased from 20 μm to 60 μm which is the optimum value for the selected flow rates- the minimum length requirement for the optimum burner is attributed to the rapid axial development of the combustion rate rather than the fast vaporization rate. The present approach can be used for all cryogenic propellants, partially cryogenic or non- cryogenic bipropellant combinations.

UR - http://www.scopus.com/inward/record.url?scp=84997284753&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84997284753&partnerID=8YFLogxK

M3 - Paper

AN - SCOPUS:84997284753

T2 - AIAA/ASME/SAE/ASEE 23rd Joint Propulsion Conference, 1987

Y2 - 29 June 1987 through 2 July 1987

ER -