SUPERSONIC TRANSPORT ENGINE DEVELOPMENT. APPENDIX A. FUEL CONTROL SYSTEM STUDY.

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Abstract:

The control design which was evolved during Phase I was reviewed in more detail from the standpoint of reliability, maintenance features, effect on engine plumbing, disassembly and assembly techniques, size, weight and materials, and economic considerations in the design approach. Detailed investigations were conducted in areas in which design substantiation was considered to be necessary. Developmental testing was specifically directed toward continuing the evaluation of the fan pressure-ratio sensor and the fluid state latch mechanism which had been fabricated during the previous phase. The testing was intended to determine the performance capability of the two critical subsystems under SST environmental conditions of pressure, temperature, and vibration.

Author(s):
No Author(s) Identified
Author Organization(s):
PRATT AND WHITNEY AIRCRAFT GROUP EAST HARTFORD CT
Descriptive Note:
Final rept. on Phase 2A.
Supplementary Note:
Prepared in cooperation with Bendix Products Aerospace Div., South Bend, Ind. Rept. no. BPAD-863-15177-R. See also Appendix B, AD-804 056L.
Pagination:
0146

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
PWA-2397-App-A
Contract/Grant Number(s):
FA-SS-64-2
 Subject Terms
Communities of Interest:
Space
Descriptor(s):
*JET TRANSPORT AIRCRAFT, *TURBOFAN ENGINES, SUPERSONIC AIRCRAFT, FUEL SYSTEMS, COMMERCIAL AIRCRAFT, FUEL CONSUMPTION, CONTROL SYSTEMS, RELIABILITY, MAINTENANCE, ASSEMBLY, WEIGHT, PERFORMANCE(ENGINEERING), PRESSURE, TEMPERATURE, VIBRATION
Field(s)/Group(s):
Civilian Aircraft, Jet and Gas Turbine Engines
Keyword(s):
ENGINE CONTROL SYSTEMS, SUPERSONIC TRANSPORTS
Report Date:
1964 Oct 15