Application of a High-temperature Static Strain Gage to the Measurement of Thermal Stresses in a Turbine Stator Vane PDF Download
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Author: R. H. Kemp Publisher: ISBN: Category : Turbines Languages : en Pages : 36
Book Description
The thermal stresses in a turbine stator vane of a turbojet engine were measured by means of static high-temperature resistance-wire strain gages. The temperature variations existing in the engine were duplicated in the vane in a test setup at a reduced average temperature. Stress measurements at the leading and trailing edges indicated maximum principal values in compression of 18,100 and 27,200 psi, respectively. In the midchord region on the suction surface, the maximum principal stress was 19,600 psi in compression and in the midchord region on the pressure surface, 26,200 psi in tension.
Author: R. H. Kemp Publisher: ISBN: Category : Turbines Languages : en Pages : 36
Book Description
The thermal stresses in a turbine stator vane of a turbojet engine were measured by means of static high-temperature resistance-wire strain gages. The temperature variations existing in the engine were duplicated in the vane in a test setup at a reduced average temperature. Stress measurements at the leading and trailing edges indicated maximum principal values in compression of 18,100 and 27,200 psi, respectively. In the midchord region on the suction surface, the maximum principal stress was 19,600 psi in compression and in the midchord region on the pressure surface, 26,200 psi in tension.
Author: Stanley Faber Publisher: ISBN: Category : Airplanes Languages : en Pages : 680
Book Description
In this study in which an airplane simulator with one degree of freedom (pitch) was used, results were determined for three conditions of airplane dynamics. For an undamped natural frequency of 1/2 cps with a damping ratio of 0.18 and for an undamped natural frequency of 1 cps with a damping ratio of 0.11, moderate longitudinal stick forces and displacements were desired.
Author: Naval Air Material Center, Philadelphia. Aeronautical Structures Laboratory Publisher: ASTM International ISBN: Category : Languages : en Pages : 170
Author: B. R. Anderson Publisher: ISBN: Category : Airplanes Languages : en Pages : 9
Book Description
This paper covers recent advancements in the development and application of high-temperature strain gages for stress measurements in jet engines. Development of high-temperature strain gages can be divided into three areas: (1) alloys, (2) cements, and (3) fabrication and application techniques. In the Aircraft Gas Turbine Division, the measurement of vibratory stress and static stress are both of primary importance. For vibratory stress measurement, a high-temperature strain gage has been developed which will operate at temperatures up to 1500 F continuously and up to 1800 F for short periods of time. For static stress measurement, a self-temperature -- compensating, high -- temperature strain gage has been developed for application on specific alloys up to 850 F. Developments to increase the temperature range of both of these gages are under way.
Author: R. H. Kemp
Author: R. H. Kemp
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: Stanley Faber
Author: Naval Air Material Center, Philadelphia. Aeronautical Structures Laboratory
Author: Patrick T. Chiarito
Author: J. R. Johnston
Author: B. R. Anderson
Author: