Accession Number : ADA157108


Title :   Compressor Research Facility F100 High Pressure Compressor Inlet Total Pressure and Swirl Profile Simulation.


Descriptive Note : Final rept. Dec 80-Nov 83,


Corporate Author : AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH


Personal Author(s) : Copenhaver,W W


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a157108.pdf


Report Date : Oct 1984


Pagination or Media Count : 287


Abstract : The F100 gas turbine engine currently powers the Air Force F-15 and F-16 aircraft. The compression section of this engine consists of a three-stage fan followed by a ten-stage High Pressure Compressor (HPC). A component test od the F100 HPC will be performed in the Compressor Research Facility (CRF) of the Aero Propulsion Laboratory (APL) at Wright-Patterson Air Force Base, to investigate its stall and post stall characteristics. This testing will require that the high pressure compressor entrance profiles be simulated to obtain results which correspond to actual engine operation. Since these entrance profiles had never been measured, a program was designed to experimentally measure the total and static pressure, temperature and flow angle profiles at the HPC entrance of an F100 Series 3 engine (F100 (3)), (S/NP072). The measured profile data were then used as design data for a set of inlet screens and vanes. These vanes and screens will simulate the engine fan discharge profiles for the HPC test. The manufactured screens and vanes were tested in Room 24 of Building 18 of the Air Force Wright Aeronautical Laboratories to verify their simulation capabilities. Five separate test periods were necessary to achieve the program goals. These tests are described in Sections II thru VI. The program discussion and conclusions are presented in Section VII and VIII. Additional keywords: F-100 engine; aerodynamic tests; Swirler vanes; Inlet guide vanes; preswirl vanes.


Descriptors :   *TURBOFAN ENGINES , *HIGH PRESSURE COMPRESSORS , *JET ENGINE INLETS , COMPRESSION , SIMULATION , ANGLES , TEST METHODS , RESEARCH FACILITIES , STALLING , PROFILES , OPERATION , JET FIGHTERS , ENGINES , FANS , FLOW , COMPRESSORS , STATIC PRESSURE , PRESSURE DISTRIBUTION , DYNAMIC PRESSURE , SWIRLER VANES , INLET GUIDE VANES


Subject Categories : Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE