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2.14 ENGINE.
The T700 engine (Figure 2-9), is a front drive, turboshaft engine of modular construction. One is mounted on the airframe at either side of the main transmission. The engine is divided into four modules: cold section, hot section, power turbine section, and accessory section.
2.14.1 Cold Section Module. The cold section module (Figure 2-9), includes the inlet particle separator, the com-
pressor, the output shaft assembly, and line replaceable units (LRU’s). The inlet particle separator removes sand, dust, and other foreign material from the engine inlet air. Engine inlet air passes through the swirl vanes, spinning the air and throwing dirt out by inertial action into the collector scroll, after which it is sucked through by the engine-driven blower and discharged overboard around the engine exhaust duct. The compressor has .ve axial stages and one centrifu-gal stage. There are variable inlet guide vanes and variable stage 1 and stage 2 vanes. LRU’s mounted on the cold section module are the electrical control unit (ECU), anti-icing and start bleed valve, history recorder, ignition sys-tem, and electrical cables.
2.14.2 Hot Section Module. The hot section module (Figure 2-9) consists of three subassemblies; the gas gen-
erator turbine, stage 1 nozzle assembly, and combustion liner. LRU’s on the hot section module are primer nozzles and ignitors. The gas generator turbine consists of a gas generator stator assembly and a two-stage air cooled tur-bine rotor assembly which drives the compressor and the accessory gear box. Stage 1 nozzle assembly contains air cooled nozzle segments. The nozzle assemblies direct gas .ow to the gas generator turbine. The combustion liner is a ring type combustor cooled by air .ow from the diffuser case.
2.14.3 Power Turbine Section Module. The power turbine module (Figure 2-9), includes a two stage power turbine, exhaust frame, and the shaft and C-sump assembly. The LRU’s mounted on the power turbine section module are the thermocouple harness, torque and overspeed sensor, and Np (% RPM 1 or 2) sensor.
2.14.4 Accessory Section Module. The accessory section module (Figure 2-9) includes the top mounted accessory gear box and a number of LRU’s. The LRUs mounted on the module are the hydromechanical unit (HMU), engine driven boost pump, oil .lter, oil cooler, alternator, oil and scavenge pump, particle separator blower, fuel .lter assembly, chip detector, oil .lter bypass sensor, radial drive shaft, fuel pressure sensor, and oil pres-sure sensor.
2.15 ENGINE FUEL SUPPLY SYSTEM.
The engine fuel supply system consists primarily of the low pressure engine driven boost pump, fuel .lter, fuel .l-ter bypass valve, fuel pressure sensor, hydromechanical unit (HMU), pressurizing and overspeed unit (POU).
2.15.1 Engine Driven Boost Pump. A low pressure suction engine driven boost pump is installed on the front face of the engine accessory gear box (Figure 2-9). It assures that the airframe fuel supply system is under nega-tive pressure, lessening the potential of .re in case of fuel system damage. Lighting of the #1 or #2 FUEL PRESS caution legend at idle speed and above could indicate a leak, or failed engine driven boost pump.
2.15.2 Fuel Filter. The fuel .lter is a barrier type full .ow .lter with integral bypass. An electrical switch lights the #1 FUEL FLTR BYPAS or #2 FUEL FLTR BYPAS caution legend to indicate .lter bypass. In addition, a red button on the .lter housing pops out when .lter element differential pressure indicates impending bypass. Power for the fuel .lter bypass legends is from the No. 1 and No. 2 dc primary busses through circuit breakers marked NO. 1 and NO. 2 ENG WARN LTS respectively.
2.15.3 Fuel Pressure Warning System. The engine fuel pressure warning system for each engine consists of a pressure switch that turns on the FUEL PRESS caution legend. Fuel pressure caution legends, marked #1 FUEL PRESS and #2 FUEL PRESS will light when fuel pres-sure drops below 9 psi. This legend can go on when fuel pressure drops, due to failure of the low pressure boost pump or an air leak in the suction fuel system. The effect will vary depending upon the size of the leak. The effect will be more serious at low engine power. A large enough leak may cause a .ameout. Power for the No. 1 engine fuel pressure warning system is supplied by the No. 1 dc pri-mary bus through the NO. 1 ENG WARN LTS circuit breaker. Power for the No. 2 engine fuel pressure warning system is supplied by the No. 2 dc primary bus through the NO. 2 ENG WARN LTS circuit breaker.
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UH-60Q 直升机技术手册 直升机操作手册 1(18)
