Flow path and interaction analysis in a hydrogen transpiration cooled scramjet model combustor

Friedolin T. Strauss; Stephan General; Chiara Manfletti; Stefan Schlechtriem

doi:10.2514/6.2019-4015

Flow path and interaction analysis in a hydrogen transpiration cooled scramjet model combustor

Friedolin T. Strauss, Stephan General, Chiara Manfletti, Stefan Schlechtriem

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

5 Scopus citations

Abstract

Cooling experiments are performed by the DLR Institute of Space Propulsion, applying a transpiration cooling system to a scramjet model combustion chamber. Hydrogen coolant is injected through different porous wall samples made of sintered stainless steel into a Mach 2.5 hot gas main flow. Different inlet conditions as well as the response of the transpiration cooling to a shock impingement caused by a 9.3° half wedge at different lateral positions are investigated by means of Background Oriented Schlieren (BOS). Results show good transpiration cooling efficiency which is governed by the impinging shock and its position. Limitations and encountered flow phenomena of this cooling approach are also discussed.

Original language	English
Title of host publication	AIAA Propulsion and Energy Forum and Exposition, 2019
Publisher	American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)	9781624105906
DOIs	https://doi.org/10.2514/6.2019-4015
State	Published - 2019
Externally published	Yes
Event	AIAA Propulsion and Energy Forum and Exposition, 2019 - Indianapolis, United States Duration: 19 Aug 2019 → 22 Aug 2019

Publication series

Name	AIAA Propulsion and Energy Forum and Exposition, 2019

Conference

Conference	AIAA Propulsion and Energy Forum and Exposition, 2019
Country/Territory	United States
City	Indianapolis
Period	19/08/19 → 22/08/19

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10.2514/6.2019-4015

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Strauss, F. T., General, S., Manfletti, C., & Schlechtriem, S. (2019). Flow path and interaction analysis in a hydrogen transpiration cooled scramjet model combustor. In AIAA Propulsion and Energy Forum and Exposition, 2019 (AIAA Propulsion and Energy Forum and Exposition, 2019). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2019-4015

@inproceedings{9b34c588120b42eab606c820a214a307,

title = "Flow path and interaction analysis in a hydrogen transpiration cooled scramjet model combustor",

abstract = "Cooling experiments are performed by the DLR Institute of Space Propulsion, applying a transpiration cooling system to a scramjet model combustion chamber. Hydrogen coolant is injected through different porous wall samples made of sintered stainless steel into a Mach 2.5 hot gas main flow. Different inlet conditions as well as the response of the transpiration cooling to a shock impingement caused by a 9.3° half wedge at different lateral positions are investigated by means of Background Oriented Schlieren (BOS). Results show good transpiration cooling efficiency which is governed by the impinging shock and its position. Limitations and encountered flow phenomena of this cooling approach are also discussed.",

author = "Strauss, {Friedolin T.} and Stephan General and Chiara Manfletti and Stefan Schlechtriem",

note = "Publisher Copyright: {\textcopyright} 2019 by American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.; AIAA Propulsion and Energy Forum and Exposition, 2019 ; Conference date: 19-08-2019 Through 22-08-2019",

year = "2019",

doi = "10.2514/6.2019-4015",

language = "English",

isbn = "9781624105906",

series = "AIAA Propulsion and Energy Forum and Exposition, 2019",

publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",

booktitle = "AIAA Propulsion and Energy Forum and Exposition, 2019",

}

Strauss, FT, General, S, Manfletti, C & Schlechtriem, S 2019, Flow path and interaction analysis in a hydrogen transpiration cooled scramjet model combustor. in AIAA Propulsion and Energy Forum and Exposition, 2019. AIAA Propulsion and Energy Forum and Exposition, 2019, American Institute of Aeronautics and Astronautics Inc, AIAA, AIAA Propulsion and Energy Forum and Exposition, 2019, Indianapolis, United States, 19/08/19. https://doi.org/10.2514/6.2019-4015

Flow path and interaction analysis in a hydrogen transpiration cooled scramjet model combustor. / Strauss, Friedolin T.; General, Stephan; Manfletti, Chiara et al.
AIAA Propulsion and Energy Forum and Exposition, 2019. American Institute of Aeronautics and Astronautics Inc, AIAA, 2019. (AIAA Propulsion and Energy Forum and Exposition, 2019).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

TY - GEN

T1 - Flow path and interaction analysis in a hydrogen transpiration cooled scramjet model combustor

AU - Strauss, Friedolin T.

AU - General, Stephan

AU - Manfletti, Chiara

AU - Schlechtriem, Stefan

PY - 2019

Y1 - 2019

N2 - Cooling experiments are performed by the DLR Institute of Space Propulsion, applying a transpiration cooling system to a scramjet model combustion chamber. Hydrogen coolant is injected through different porous wall samples made of sintered stainless steel into a Mach 2.5 hot gas main flow. Different inlet conditions as well as the response of the transpiration cooling to a shock impingement caused by a 9.3° half wedge at different lateral positions are investigated by means of Background Oriented Schlieren (BOS). Results show good transpiration cooling efficiency which is governed by the impinging shock and its position. Limitations and encountered flow phenomena of this cooling approach are also discussed.

AB - Cooling experiments are performed by the DLR Institute of Space Propulsion, applying a transpiration cooling system to a scramjet model combustion chamber. Hydrogen coolant is injected through different porous wall samples made of sintered stainless steel into a Mach 2.5 hot gas main flow. Different inlet conditions as well as the response of the transpiration cooling to a shock impingement caused by a 9.3° half wedge at different lateral positions are investigated by means of Background Oriented Schlieren (BOS). Results show good transpiration cooling efficiency which is governed by the impinging shock and its position. Limitations and encountered flow phenomena of this cooling approach are also discussed.

UR - http://www.scopus.com/inward/record.url?scp=85095977995&partnerID=8YFLogxK

U2 - 10.2514/6.2019-4015

DO - 10.2514/6.2019-4015

M3 - Conference contribution

AN - SCOPUS:85095977995

SN - 9781624105906

T3 - AIAA Propulsion and Energy Forum and Exposition, 2019

BT - AIAA Propulsion and Energy Forum and Exposition, 2019

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

T2 - AIAA Propulsion and Energy Forum and Exposition, 2019

Y2 - 19 August 2019 through 22 August 2019

ER -

Flow path and interaction analysis in a hydrogen transpiration cooled scramjet model combustor

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