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

Preliminary Thermomechanical Design for Aero-Engine combustors made of CMCs

Hönig, Sandrine and Hofmann, Severin and Behrendt, Thomas and Shi, Yuan and Koch, Dietmar (2015) Preliminary Thermomechanical Design for Aero-Engine combustors made of CMCs. 90th DKG Annual Conference & Symposium on High-Performance Ceramics 2015, 2015-03-15 - 2015-03-19, Bayreuth, Deutschland. (Unpublished)

Full text not available from this repository.


An efficient preliminary design is a competitive advantage in the development of an aero-engine. It has the potential of a significant decrease of development costs and time. In the frame work of the DLR programmes EVITA and PEGASUS, the software tool “CoSMA” (Combustor Strength and Modal Analysis) was developed for the thermomechanical design of lean combustors. Due to higher allowable material temperatures in comparison to state-of the art nickel-base alloys, ceramic matrix composites (CMCs) offer the chance for combustors with reduced cooling air consumption and lower NOx emissions. CMCs were implemented into the combustor design tool CoSMA. A combustor geometry and a temperature field in the combustor wall were generated by the combustor design tool “ComDAT” (Combustor pre-Design and Analysis Tool). In a first part, this paper presents the process of the CoSMA tool and the method used for calculating static thermal stresses, eigenfrequencies and failure criteria. In a second part, analytical methods for efficiently preselecting a material and for simple stress estimations in thermomechanically loaded liners are evaluated. Finally, an application example and a comparison to experimental combustor test results are detailed. This work shows the potential of cost-effective preliminary design tools for lean combustors. Moreover an analytical method is given for the stress estimation of effusion cooled combustors.

Item URL in elib:https://elib.dlr.de/101838/
Document Type:Conference or Workshop Item (Speech)
Title:Preliminary Thermomechanical Design for Aero-Engine combustors made of CMCs
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Behrendt, ThomasUNSPECIFIEDhttps://orcid.org/0000-0002-4154-3277UNSPECIFIED
Shi, YuanUNSPECIFIEDhttps://orcid.org/0000-0002-4210-9069UNSPECIFIED
Koch, DietmarUNSPECIFIEDhttps://orcid.org/0000-0003-4504-8721UNSPECIFIED
Date:March 2015
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:FEM, thermomechanical analysis, combustor, liner, CMC, ceramic matrix composite, WHIPOX
Event Title:90th DKG Annual Conference & Symposium on High-Performance Ceramics 2015
Event Location:Bayreuth, Deutschland
Event Type:national Conference
Event Start Date:15 March 2015
Event End Date:19 March 2015
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:propulsion systems
DLR - Research area:Aeronautics
DLR - Program:L ER - Engine Research
DLR - Research theme (Project):L - Combusion Chamber Technologies (old)
Location: Köln-Porz , Stuttgart
Institutes and Institutions:Institute of Structures and Design > Ceramic Composite Structures
Institute of Propulsion Technology > Combustor
Deposited By: Hönig, Dipl.-Ing. Sandrine
Deposited On:13 Jan 2016 12:44
Last Modified:24 Apr 2024 20:07

Repository Staff Only: item control page

Help & Contact
electronic library is running on EPrints 3.3.12
Website and database design: Copyright © German Aerospace Center (DLR). All rights reserved.