NDLI: Rl10 ignition limits test for shuttle centaur

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Rl10 ignition limits test for shuttle centaur

Content Provider	NASA Technical Reports Server (NTRS)
Copyright Year	1987
Description	During routine development testing of the RL10A-3-3B engine a potential no-ignition condition was encountered when operating at certain propellant inlet conditions within the Shuttle Centaur G operating region. The conditions, the resulting investigative program, and methods to correct the potential problem are discussed. The Shuttle Centaur program was cancelled prior to completion of this effort. Although the RL10 engine in the Atlas Centaur vehicle is required by specification to operate over a wide range of propellant inlet conditions. The vehicle actually operates over a narrow range of conditions. This factor, combined with configuration differences between Atlas Centaur (or Titan Centaur) and the Shuttle Centaur RL10 engines, indicates the ignition problem does not exist for these vehicles. As a precautionary measure the vehicle manufacturer was requested to coordinate with Pratt and Whitney any anticipated changes in propellant inlet conditions from the current narrow range. An engineering change will be proposed for future RL10 deliveries to provide more consistent propellant flow to the igniter. This will permit operation of the engine throughout the wide range specification inlet conditions if desired.
File Size	2671742
Page Count	61
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19910001736
Archival Resource Key	ark:/13960/t5m953w14
Language	English
Publisher Date	1987-05-01
Access Restriction	Open
Subject Keyword	Spacecraft Propulsion And Power Performance Tests Ignition Ignition Limits Titan Launch Vehicles Inlet Flow Engine Tests Atlas Centaur Launch Vehicle Graphs Charts Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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