NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Engine Hydraulic StabilityAn analytical injector model was developed specifically to analyze combustion instability coupling between the injector hydraulics and the combustion process. This digital computer dynamic injector model will, for any imposed chamber of inlet pressure profile with a frequency ranging from 100 to 3000 Hz (minimum) accurately predict/calculate the instantaneous injector flowrates. The injector system is described in terms of which flow segments enter and leave each pressure node. For each flow segment, a resistance, line lengths, and areas are required as inputs (the line lengths and areas are used in determining inertance). For each pressure node, volume and acoustic velocity are required as inputs (volume and acoustic velocity determine capacitance). The geometric criteria for determining inertances of flow segments and capacitance of pressure nodes was set. Also, a technique was developed for analytically determining time averaged steady-state pressure drops and flowrates for every flow segment in an injector when such data is not known. These pressure drops and flowrates are then used in determining the linearized flow resistance for each line segment of flow.
Document ID
19770023226
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Kesselring, R. C.
(Rockwell International Corp. Canoga Park, CA, United States)
Sprouse, K. M.
(Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
September 3, 2013
Publication Date
July 1, 1977
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-CR-151499
R-77-159
Report Number: NASA-CR-151499
Report Number: R-77-159
Accession Number
77N30170
Funding Number(s)
CONTRACT_GRANT: NAS9-14801
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
No Preview Available