Performance test of micro turbojet engine's evaporator and numerical simulation of the combustor

Wen Long Tan; Wei Jun Fan; Tao Zhang; Wei Jian Wang; Rong Chun Zhang

Performance test of micro turbojet engine's evaporator and numerical simulation of the combustor

Wen Long Tan^*
, Wei Jun Fan
, Tao Zhang
, Wei Jian Wang
, Rong Chun Zhang

^*Corresponding author for this work

Beihang University

Research output: Contribution to journal › Article › peer-review

7 Scopus citations

Abstract

An annular combustor supplied by evaporator for a micro turbojet engine which was used for 40 daN level missile was designed. The evaporator's atomization and evaporation rate data was obtaind by test and then used for the numerical simulation of the combustor. The CFD(computational fluid dynamics) simulation shows the structure of the combustor is reasonable and the performance meets the design point's requirements.

Original language	English
Pages (from-to)	861-867
Number of pages	7
Journal	Hangkong Dongli Xuebao/Journal of Aerospace Power
Volume	27
Issue number	4
State	Published - Apr 2012

Keywords

Combustor
Evaporator
Micro turbojet engine
Numerical simulation
Performance test

Cite this

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title = "Performance test of micro turbojet engine's evaporator and numerical simulation of the combustor",

abstract = "An annular combustor supplied by evaporator for a micro turbojet engine which was used for 40 daN level missile was designed. The evaporator's atomization and evaporation rate data was obtaind by test and then used for the numerical simulation of the combustor. The CFD(computational fluid dynamics) simulation shows the structure of the combustor is reasonable and the performance meets the design point's requirements.",

keywords = "Combustor, Evaporator, Micro turbojet engine, Numerical simulation, Performance test",

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year = "2012",

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AU - Fan, Wei Jun

AU - Zhang, Tao

AU - Wang, Wei Jian

AU - Zhang, Rong Chun

PY - 2012/4

Y1 - 2012/4

N2 - An annular combustor supplied by evaporator for a micro turbojet engine which was used for 40 daN level missile was designed. The evaporator's atomization and evaporation rate data was obtaind by test and then used for the numerical simulation of the combustor. The CFD(computational fluid dynamics) simulation shows the structure of the combustor is reasonable and the performance meets the design point's requirements.

AB - An annular combustor supplied by evaporator for a micro turbojet engine which was used for 40 daN level missile was designed. The evaporator's atomization and evaporation rate data was obtaind by test and then used for the numerical simulation of the combustor. The CFD(computational fluid dynamics) simulation shows the structure of the combustor is reasonable and the performance meets the design point's requirements.

KW - Combustor

KW - Evaporator

KW - Micro turbojet engine

KW - Numerical simulation

KW - Performance test

UR - https://www.scopus.com/pages/publications/84861956267

M3 - 文章

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SN - 1000-8055

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JO - Hangkong Dongli Xuebao/Journal of Aerospace Power

JF - Hangkong Dongli Xuebao/Journal of Aerospace Power

IS - 4

ER -

Performance test of micro turbojet engine's evaporator and numerical simulation of the combustor

Abstract

Keywords

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