Failure mechanism and life evaluation of liquid rocket engine combustion chamber under severe multi-physics conditions
In Japan, new developments of liquid rocket engines are now underway for Japan's next flagship launch system. In the development, front-loading design process is applied to reduce development costs and to increase reliability. Therefore it is indispensable to precisely evaluate life time of...
| Main Authors: | , , , , , , , |
|---|---|
| Format: | Article |
| Language: | Japanese |
| Published: |
The Japan Society of Mechanical Engineers
2015-05-01
|
| Series: | Nihon Kikai Gakkai ronbunshu |
| Subjects: | |
| Online Access: | https://www.jstage.jst.go.jp/article/transjsme/81/826/81_14-00674/_pdf/-char/en |
| _version_ | 1828192584555560960 |
|---|---|
| author | Miki NISHIMOTO Hideyo NEGISHI Shinobu YOSHIMURA Naoto KASAHARA Hiroshi AKIBA Hideo SUNAKAWA Shusuke HORI Nobuki NEGORO |
| author_facet | Miki NISHIMOTO Hideyo NEGISHI Shinobu YOSHIMURA Naoto KASAHARA Hiroshi AKIBA Hideo SUNAKAWA Shusuke HORI Nobuki NEGORO |
| author_sort | Miki NISHIMOTO |
| collection | DOAJ |
| description | In Japan, new developments of liquid rocket engines are now underway for Japan's next flagship launch system. In the development, front-loading design process is applied to reduce development costs and to increase reliability. Therefore it is indispensable to precisely evaluate life time of a combustion chamber, which is exposed to the most severe heat and loads among engine components, in an early design phase. In order to improve accuracy in the life prediction, we focus on the interaction between thermo-fluid behaviors and structural responses, and have been developing the multi-physics coupled simulation. By applying this simulation and the linear damage rule, we have clarified the mechanisms and the dominant factors of cracks occurred in the throat, which were experienced under development of the upper stage engine. It has been revealed that the damage is caused by creep and low cycle fatigue and depends on structural temperature histories. Structural temperature overshoots in the start-up process are affected by the transient flows of both combustion gas and coolant. Due to overshooting temperature, creep and low cycle fatigue damage are accumulated. |
| first_indexed | 2024-04-12T08:56:40Z |
| format | Article |
| id | doaj.art-f77475008a7d44ed80a8a71ae7d81725 |
| institution | Directory Open Access Journal |
| issn | 2187-9761 |
| language | Japanese |
| last_indexed | 2024-04-12T08:56:40Z |
| publishDate | 2015-05-01 |
| publisher | The Japan Society of Mechanical Engineers |
| record_format | Article |
| series | Nihon Kikai Gakkai ronbunshu |
| spelling | doaj.art-f77475008a7d44ed80a8a71ae7d817252022-12-22T03:39:23ZjpnThe Japan Society of Mechanical EngineersNihon Kikai Gakkai ronbunshu2187-97612015-05-018182614-0067414-0067410.1299/transjsme.14-00674transjsmeFailure mechanism and life evaluation of liquid rocket engine combustion chamber under severe multi-physics conditionsMiki NISHIMOTO0Hideyo NEGISHI1Shinobu YOSHIMURA2Naoto KASAHARA3Hiroshi AKIBA4Hideo SUNAKAWA5Shusuke HORI6Nobuki NEGORO7Japan Aerospace Exploration AgencyJapan Aerospace Exploration AgencyDepartment of Systems Innovation, The University of TokyoDepartment of Nuclear Engineering and Management, The University of TokyoAllied Engineering CorporationJapan Aerospace Exploration AgencyJapan Aerospace Exploration AgencyJapan Aerospace Exploration AgencyIn Japan, new developments of liquid rocket engines are now underway for Japan's next flagship launch system. In the development, front-loading design process is applied to reduce development costs and to increase reliability. Therefore it is indispensable to precisely evaluate life time of a combustion chamber, which is exposed to the most severe heat and loads among engine components, in an early design phase. In order to improve accuracy in the life prediction, we focus on the interaction between thermo-fluid behaviors and structural responses, and have been developing the multi-physics coupled simulation. By applying this simulation and the linear damage rule, we have clarified the mechanisms and the dominant factors of cracks occurred in the throat, which were experienced under development of the upper stage engine. It has been revealed that the damage is caused by creep and low cycle fatigue and depends on structural temperature histories. Structural temperature overshoots in the start-up process are affected by the transient flows of both combustion gas and coolant. Due to overshooting temperature, creep and low cycle fatigue damage are accumulated.https://www.jstage.jst.go.jp/article/transjsme/81/826/81_14-00674/_pdf/-char/enrocket enginecombustion chamberfailure modethermal stresscreep fatigue fractureresidual deformationmulti-physics simulationlinear damage rule |
| spellingShingle | Miki NISHIMOTO Hideyo NEGISHI Shinobu YOSHIMURA Naoto KASAHARA Hiroshi AKIBA Hideo SUNAKAWA Shusuke HORI Nobuki NEGORO Failure mechanism and life evaluation of liquid rocket engine combustion chamber under severe multi-physics conditions Nihon Kikai Gakkai ronbunshu rocket engine combustion chamber failure mode thermal stress creep fatigue fracture residual deformation multi-physics simulation linear damage rule |
| title | Failure mechanism and life evaluation of liquid rocket engine combustion chamber under severe multi-physics conditions |
| title_full | Failure mechanism and life evaluation of liquid rocket engine combustion chamber under severe multi-physics conditions |
| title_fullStr | Failure mechanism and life evaluation of liquid rocket engine combustion chamber under severe multi-physics conditions |
| title_full_unstemmed | Failure mechanism and life evaluation of liquid rocket engine combustion chamber under severe multi-physics conditions |
| title_short | Failure mechanism and life evaluation of liquid rocket engine combustion chamber under severe multi-physics conditions |
| title_sort | failure mechanism and life evaluation of liquid rocket engine combustion chamber under severe multi physics conditions |
| topic | rocket engine combustion chamber failure mode thermal stress creep fatigue fracture residual deformation multi-physics simulation linear damage rule |
| url | https://www.jstage.jst.go.jp/article/transjsme/81/826/81_14-00674/_pdf/-char/en |
| work_keys_str_mv | AT mikinishimoto failuremechanismandlifeevaluationofliquidrocketenginecombustionchamberunderseveremultiphysicsconditions AT hideyonegishi failuremechanismandlifeevaluationofliquidrocketenginecombustionchamberunderseveremultiphysicsconditions AT shinobuyoshimura failuremechanismandlifeevaluationofliquidrocketenginecombustionchamberunderseveremultiphysicsconditions AT naotokasahara failuremechanismandlifeevaluationofliquidrocketenginecombustionchamberunderseveremultiphysicsconditions AT hiroshiakiba failuremechanismandlifeevaluationofliquidrocketenginecombustionchamberunderseveremultiphysicsconditions AT hideosunakawa failuremechanismandlifeevaluationofliquidrocketenginecombustionchamberunderseveremultiphysicsconditions AT shusukehori failuremechanismandlifeevaluationofliquidrocketenginecombustionchamberunderseveremultiphysicsconditions AT nobukinegoro failuremechanismandlifeevaluationofliquidrocketenginecombustionchamberunderseveremultiphysicsconditions |