Development of a Hot Gas Vane Motor for Aircraft Starting Systems 861714
Design, analyses, and tests have been conducted on a double-cavity (pressure-balanced) hot gas vane motor suitable for aircraft APU starting over the temperature range of −65°F to +130°F (−54° to +54°C).
Testing of the motor was accomplished with H-70 (70% hydrazine, 30% water) monopropellant hot gas decomposition products.
Motor development focused on testing minor modifications aimed at eliminating vane breakage. The performance goals (zero to 8,800 rpm in 8 to 10 seconds) were achieved after approximately 40 tests. Hot restarts and starts at the extreme temperatures have also been demonstrated.
Citation: Dusenberry, G. and Carlson, D., "Development of a Hot Gas Vane Motor for Aircraft Starting Systems," SAE Technical Paper 861714, 1986, https://doi.org/10.4271/861714. Download Citation
Author(s):
G. Dusenberry, D. Carlson
Affiliated:
Rocket Research Co.
Pages: 12
Event:
SAE Aerospace Technology Conference and Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
Starting Systems Technology Ii-SP-0678
Related Topics:
Starters and starting
Aircraft
Gases
Hydrazines
Water
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