Spectroscopy-based thrust sensor for high-speed gaseous flows
AssigneeThe Board of Trustees of the Leland Stanford Jr. University
InventorRonald K. Hanson
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Abstract
A system and method for non-intrusively obtaining the thrust value of combustion by-products of a jet engine is disclosed herein. The system includes laser elements for inducing absorption for use in determining the axial velocity and density of the jet flow stream and elements for calculating the thrust value therefrom.
Claims18
A system for non-intrusively determining the thrust of a jet combustor apparatus having an exit end wherein combustible gas by-products are released into the ambient environment, comprising:
- axial velocity measurement means for measuring the axial velocity of at least one species of said combustion by-products and generating an axial velocity output signal;
- mass flow rate measurement means for measuring the mass flow rate of said species of combustion by-products and generating a mass flow rate output signal;
- thrust calculation means for receiving said axial velocity output signal and said mass flow rate output signal and providing a signal representing said thrust.
A method for non-intrusively determining the thrust of a jet combustor apparatus having an exit end wherein combustible gas by-products are released into the ambient environment, comprising the steps of:
- measuring the axial velocity of at least one species said combustion by-products and generating an axial velocity output signal;
- measuring the mass flow rate of said species of combustion by-products and providing a mass flow rate output signal;
- multiplying said axial velocity output signal with said mass flow rate output signal to provide a signal representing said thrust.
Dependencies are inferred from the claim text.