Open AccessStructurally compliant rocket engine combustion chamber - Experimental and analytical validation
Author(s) -
Robert S. Janovsky,
Vinod K. Arya,
John M. Kazaroff,
Gary R. Halford
Publication year - 1995
Publication title -
journal of spacecraft and rockets
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.758
H-Index - 79
eISSN - 1533-6794
pISSN - 0022-4650
DOI - 10.2514/3.26665
Subject(s) - aerospace engineering , spacecraft , missile , rocket engine , rocket (weapon) , spacecraft design , space (punctuation) , space shuttle , space station freedom , systems engineering , mechanical engineering , combustion chamber , propellant , space exploration , space vehicle , engineering , aeronautics , computer science , combustion , chemistry , organic chemistry , operating system
A new, structurally compliant rocket engine combustion chamber design has been validated through analysis and experiment. Subscale, tubular channel chambers have been cyclically tested and analytically evaluated. Cyclic lives were determined to have a potential for 1000 percent increase over those of rectangular channel designs, the current state of the art. Greater structural compliance in the circumferential direction gave rise to lower thermal strains during hot firing, resulting in lower thermal strain ratcheting and longer predicted fatigue lives. Thermal, structural, and durability analyses of the combustion chamber design, involving cyclic temperatures, strains, and low-cycle fatigue lives, have corroborated the experimental observations.
Accelerating Research
Robert Robinson Avenue,
Oxford Science Park, Oxford
OX4 4GP, United Kingdom
Address
John Eccles HouseRobert Robinson Avenue,
Oxford Science Park, Oxford
OX4 4GP, United Kingdom