elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Testing of DLR C/C-SiC and C/C for HIFIRE 8 Scramjet Combustor

Glass, David E. and Capriotti, Diego P. and Reimer, Thomas and Kütemeyer, Marius and Smart, Michael K. (2014) Testing of DLR C/C-SiC and C/C for HIFIRE 8 Scramjet Combustor. 19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 14.-20. Juni 2014, Atlanta, USA. DOI: 10.2514/MHYTASP14 ISBN 978-1-62410-284-4

[img] PDF
2MB

Official URL: http://arc.aiaa.org/doi/abs/10.2514/6.2014-3089

Abstract

Ceramic Matrix Composites (CMCs) have been proposed for use as lightweight hot structures in scramjet combustors. Previous studies have calculated significant weight savings by utilizing CMCs (active and passive) versus actively cooled metallic scramjet structures. Both a carbon/carbon (C/C) and a carbon/carbon-silicon carbide (C/C-SiC) material fabricated by DLR (Stuttgart, Germany) are being considered for use in a passively cooled combustor design for Hypersonic International Flight Research Experimentation (HIFiRE) 8, a joint Australia / Air Force Research Laboratory hypersonic flight program, expected to fly at Mach 7 for ~30 sec, at a dynamic pressure of 55 kPa. Flat panels of the DLR C/C and C/C-SiC materials were installed downstream of a hydrogen-fueled, dual-mode sramjet combustor and tested for several minutes at conditions simulating flight at Mach 5 and Mach 6. Gaseous hydrogen fuel was used to fuel the sramjet combustor. The test panels were instrumented with embedded Type K and Type S thermocouples. Zirconia felt insulation was used during some of the tests to reduce heat loss from the back surface and thus increase the heated surface temperature of the C/C-SiC panel ~177°C (350°F). The final C/C-SiC panel was tested for three cycles totaling over 135 sec at Mach 6 enthalpy. Slightly more erosion was observed on the C/C panel than the C/C-SiC panels, but both material systems demonstrated acceptable recession performance for the HIFiRE 8 flight.

Item URL in elib:https://elib.dlr.de/92521/
Document Type:Conference or Workshop Item (Speech)
Title:Testing of DLR C/C-SiC and C/C for HIFIRE 8 Scramjet Combustor
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Glass, David E.NASAUNSPECIFIED
Capriotti, Diego P.NASAUNSPECIFIED
Reimer, Thomasthomas.reimer (at) dlr.deUNSPECIFIED
Kütemeyer, Mariusmarius.kuetemeyer (at) dlr.deUNSPECIFIED
Smart, Michael K.University of Queensland, Brisbane, AustralienUNSPECIFIED
Date:June 2014
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
DOI :10.2514/MHYTASP14
ISBN:978-1-62410-284-4
Status:Accepted
Keywords:Ceramic Matrix Composite, CMC, hot structure, scramjet, combustor, C/C, C/C-SiC, HIFIRE, test
Event Title:19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Event Location:Atlanta, USA
Event Type:international Conference
Event Dates:14.-20. Juni 2014
Organizer:AIAA
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - Raumfahrzeugsysteme - Rückkehrtechnologie
Location: Stuttgart
Institutes and Institutions:Institute of Structures and Design > Space System Integration
Deposited By: Reimer, Thomas
Deposited On:23 Dec 2014 17:08
Last Modified:31 Jul 2019 19:49

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.