GTP 70-52 GAS TURBINE ENGINE
Model and Type
GTP 70-52 Turboshaft, 2- stage centrifugal compressor, 1 combustion chamber, 1-stage turbine
1st stage and 2nd stage single -entry impellers pressed and pinned on shaft supported in plain bearing at front and in ball bearing at rear. Radial diffuser. pressure ratio 3.3:1, and air mass flow 2.0 lb. sec, at 40,800 rpm.
Reverse air flow. 1 duplex fuel burner.
Radial inflow type. Turbine wheel with integral shaft supported in 2 ball bearings ahead of wheel. Exhaust temperature 1310 F (710C)
Fixed area single exhaust outlet.
Reduction gearbox at front of unit. Output shaft 6,000 rpm.
Electro-pneumatic type. Automatic starting. Acceleration, load and speed controls. Pneumatic exhaust temperature limiter.
AiResearch integral fuel system. Pump, 230 psi, governor, internal relief valve, and flow control with filter-all incluster.
Bendix-Seintilla or G.L.A. ignition. 1 igniter.
Dry sump system, 90 psi air cooled oil cooler, tank.
Width and height
30.0 in and 25.0 in.
Gasoline, Kerosene, JP-4,8 JP-5
Mil -L-23699, L-7808
Rating Max cont.
160shp/40,800 rpm/sea level.
Copyright © 1998 Avon Aero Supply, Inc.