Measuring and testing – Fluid pressure gauge – Combined
Reexamination Certificate
2001-05-31
2003-07-22
Williams, Hezron (Department: 2855)
Measuring and testing
Fluid pressure gauge
Combined
C073S170020
Reexamination Certificate
active
06595062
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Technical Field
This invention relates to a measurement device for aircraft testing. More particularly, this invention relates to a high temperature rake for measuring the temperature and/or pressure of supersonic exhaust flow from a jet engine.
2. Background of the Invention
The present invention is an apparatus for measuring a parameter, such as the temperature and pressure, of a high temperature supersonic flowing gaseous stream, such as an exhaust gas plume for a military jet. In order to evaluate the performance of a jet engine, the temperature and pressure profiles of the supersonic exhaust gas plume is needed. Heretofore, the prior art temperature and pressure measurement devices for supersonic flow of gaseous streams have been inaccurate. This is due in part to the shock wave or turbulence created by the temperature and pressure sensors and/or associated hardware in the flowing supersonic gaseous stream. In addition, these prior art devices have been unreliable and require extensive maintenance because of the corrosive, high temperature environments in which the devices operate.
Therefore, the need exists for a measurement device which reduces or eliminates the shock wave or turbulence caused by temperature and/or pressure sensors in the supersonic gaseous stream. The need also exists for a measurement device which gives accurate temperature and pressure measurements in corrosive, high temperature gaseous streams at supersonic flow conditions. The present invention meets these needs.
SUMMARY OF THE INVENTION
The invention is an apparatus for measuring a parameter of a corrosive, high temperature gaseous stream, such as an exhaust gas plume from a supersonic military jet engine. The apparatus includes an airfoil having edges, one or more sensors mounted to the airfoil and at least one base. Preferably, the airfoil is rotatable about its axis relative to the base to selectively position one or more sensors in a leading position relative to the exhaust gas flow path. The sensors are impinged by the exhaust gas flow path prior to the exhaust gas flowing over the airfoil to measure a parameter of the exhaust gas. Preferably, the sensors are attached to an airfoil edges and measure a parameter, such as the temperature and/or pressure, of the exhaust gas plume. The base is attached and adapted to be mounted to a supporting surface for locating the airfoil rearward of the exhaust gas plume.
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Luke Richard Stanley
McGee Mark Goldman
Pierce John William
Allen Andre
Bracewell & Patterson L.L.P.
Lockheed Martin Corporation
Williams Hezron
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