Effusion cooling of throat region in rocket engines applying fibre reinforced ceramics

Erhan Serbest; Dirk Greuel; Oskar J. Haidn; Hermann Hald; Gertrud Korger

Effusion cooling of throat region in rocket engines applying fibre reinforced ceramics

Erhan Serbest
, Dirk Greuel
, Oskar J. Haidn
, Hermann Hald
, Gertrud Korger

Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR)

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

18 Scopus citations

Abstract

This report summarizes the experimental work in the field of effusion cooling done with C/C (carbon fibres in carbon matrix) for a porous cylinder in combination with a porous nozzle. The experiments presented here have been realized using gaseous hydrogen at ambient temperature as coolant. These recent DLR experiments have been performed for combustion chamber pressures ranging between 0.8 MPa and 1.2 MPa at a constant oxidizer/fuel mixture ratio 6.5. For this basic experiments there is a micro combustor at DLR. The porosity for the cylinder and nozzle was ε = 26%. The coolant mass flow for the porous cylinder and nozzle has been varied in a wide range to get informations about the influence of the cooling film from the cylinder to the nozzle.

Original language	English
State	Published - 2001
Externally published	Yes
Event	37th Joint Propulsion Conference and Exhibit 2001 - Salt Lake City, UT, United States Duration: 8 Jul 2001 → 11 Jul 2001

Conference

Conference	37th Joint Propulsion Conference and Exhibit 2001
Country/Territory	United States
City	Salt Lake City, UT
Period	8/07/01 → 11/07/01

UN SDGs

This output contributes to the following UN Sustainable Development Goals (SDGs)

SDG 7 Affordable and Clean Energy

Cite this

@conference{99a88a051232453684b4ee3c52d71887,

title = "Effusion cooling of throat region in rocket engines applying fibre reinforced ceramics",

abstract = "This report summarizes the experimental work in the field of effusion cooling done with C/C (carbon fibres in carbon matrix) for a porous cylinder in combination with a porous nozzle. The experiments presented here have been realized using gaseous hydrogen at ambient temperature as coolant. These recent DLR experiments have been performed for combustion chamber pressures ranging between 0.8 MPa and 1.2 MPa at a constant oxidizer/fuel mixture ratio 6.5. For this basic experiments there is a micro combustor at DLR. The porosity for the cylinder and nozzle was ε = 26\%. The coolant mass flow for the porous cylinder and nozzle has been varied in a wide range to get informations about the influence of the cooling film from the cylinder to the nozzle.",

author = "Erhan Serbest and Dirk Greuel and Haidn, \{Oskar J.\} and Hermann Hald and Gertrud Korger",

year = "2001",

language = "English",

note = "37th Joint Propulsion Conference and Exhibit 2001 ; Conference date: 08-07-2001 Through 11-07-2001",

}

TY - CONF

T1 - Effusion cooling of throat region in rocket engines applying fibre reinforced ceramics

AU - Serbest, Erhan

AU - Greuel, Dirk

AU - Haidn, Oskar J.

AU - Hald, Hermann

AU - Korger, Gertrud

PY - 2001

Y1 - 2001

N2 - This report summarizes the experimental work in the field of effusion cooling done with C/C (carbon fibres in carbon matrix) for a porous cylinder in combination with a porous nozzle. The experiments presented here have been realized using gaseous hydrogen at ambient temperature as coolant. These recent DLR experiments have been performed for combustion chamber pressures ranging between 0.8 MPa and 1.2 MPa at a constant oxidizer/fuel mixture ratio 6.5. For this basic experiments there is a micro combustor at DLR. The porosity for the cylinder and nozzle was ε = 26%. The coolant mass flow for the porous cylinder and nozzle has been varied in a wide range to get informations about the influence of the cooling film from the cylinder to the nozzle.

AB - This report summarizes the experimental work in the field of effusion cooling done with C/C (carbon fibres in carbon matrix) for a porous cylinder in combination with a porous nozzle. The experiments presented here have been realized using gaseous hydrogen at ambient temperature as coolant. These recent DLR experiments have been performed for combustion chamber pressures ranging between 0.8 MPa and 1.2 MPa at a constant oxidizer/fuel mixture ratio 6.5. For this basic experiments there is a micro combustor at DLR. The porosity for the cylinder and nozzle was ε = 26%. The coolant mass flow for the porous cylinder and nozzle has been varied in a wide range to get informations about the influence of the cooling film from the cylinder to the nozzle.

UR - https://www.scopus.com/pages/publications/84894323577

M3 - Paper

AN - SCOPUS:84894323577

T2 - 37th Joint Propulsion Conference and Exhibit 2001

Y2 - 8 July 2001 through 11 July 2001

ER -

Effusion cooling of throat region in rocket engines applying fibre reinforced ceramics

Abstract

Conference

UN SDGs

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