An attempt is being made to develop a method for measuring the temperature of the turbine blades in a gas turbine during operation. Information of this temperature is essential in the design of turbines in the gas turbine field. But the methods previously used have considerable drawbacks. This paper will cover the design of a test stand and the installation of a gas turbine for use in blade temperature measurements.
A turbosupercharger and two jet propulsion burners have been assembled to form a gas turbine which operates on a constant pressure combustion cycle. The instruments selected to obtain data about the gases in the turbine consists of mercury and water manometers for pressure, and thermocouples to determine temperatures. The burners operate on fuel oil which is supplied by an auxiliary pump. The speed of the turbine can be controlled by regulating the quantity of fuel fed to the burners. The turbine is started by spinning it with steam and then igniting the fuel in the burners by spark plugs.
Provisions were made for supplying a large quantity of fresh air to the turbine, and for disposing of a larger quantity of hot exhaust gas. An external lubricating oil tank was provided, but an oil cooler and oil filter were not needed.
Safety to personnel was a problem which could not be ignored. Heavy reinforced concrete walls and steel protection for the door along with detectors to automatically shut down the turbine if symptoms of danger occur were part of the safety program. Starting, stopping, and operating procedures have been outlined and should be carefully considered.
Copyright 1947
Engine Research Center
University of Wisconsin-Madison