
The rotor with four vanes and floating pin (36) form a rotary mechanism which divides the chamber of
sleeve (19) into two spaces - suction space A (Ref. Fig. 2) and delivery space B. As the rotor rotates, the
volume of the suction and delivery spaces is continuously varying. The volume behind the vanes increases
ensuring suction of g&soline from the tanks, while in front of the vanes it decreases and gasoline under
pressure is supplied to the carburetor. During one revolution of the rotor the pumping unit takes four volumes of
gasoline at fuel pump inlet and forces them out at the fuel pump outlet.
When gasoline flow rate decreases, pressure in the delivery space rises and gasoline pressure force
acting upon the reducing valve lifts it compressing the spring. As a result some gasoline flows through the
reducing valve to the suction space and its delivery automatically decreases.
If gasoline is not consumed from the delivery space, all gasoline by-passes to the suction space, i.e. the
pump circulates the gasoline In its housing.
The gasoline pressure in the delivery space is adjusted by changing compression of the reducing valve
spring by driving in or out the adjustment screw.
Diaphragm (25) (Ref. Pig. 1) is intended for ensuring constant delivery pressure at inlet and
atmospheric pressure variations. The space above the diaphragm communicates with atmosphere through a
special vent.
When climbing and as fuel reserve decreases in the airplane tank, suction rarefaction rises. However,
since pressure drops equally both above the reducing chamber diaphragm and in the pump suction line and in
the air space of the carburetor diaphragm mechanism, the delivery pressure is maintained within required limits.
Since the priming system hand pump is installed upstream of the fuel pump, prior to starting the engine,
the fuel fed by the priming pump fills the volume above the reducing valve through holes made in the reducing
valve mushroom-type head, presses upon the priming valve, compresses its spring to open flow of fuel to the
fuel system delivery space.
Pump Operation Diagram Figure 2
1. Vane
2. Rotor
3. Sleeve
Содержание M-14P
Страница 6: ...19 Engine M 14P Front View Figure 1...
Страница 7: ...20 Engine M 14P Rear View Figure 2...
Страница 27: ...40 Arrangement of Airborne Tools in Case Figure 1...
Страница 39: ......
Страница 44: ...57 Engine M 14P Test Run Chart Figure 201...
Страница 67: ...80...
Страница 163: ...176 Crankshaft Thrust Ball Bearing Front Cover Figure 1 Intermediate Crankcase Figure 2...
Страница 166: ...179 Intermediate Grankcase Front Portion Figure 3 Intermediate Crankcase Rear Portion Figure 4...
Страница 173: ...186 Front view Cylinder Figure 1 Rear view...
Страница 174: ...187 1 Inlet Valve 2 Outer Spring 3 Inner Spring 4 Split Retainer 5 Valve Plate Inlet Valve Figure 2...
Страница 178: ...191 Intake Pipe of Cylinders Nos 4 5 and 6 Figure 4 Piston Piston Rings and Piston Pin with Plugs Figure 5...
Страница 180: ...193 Timing Mechanism Schematic Diagram Figure 6 Cam Plate Figure 7...
Страница 189: ...Blower Longitudinal Section View Figure 1...
Страница 191: ...Rear view Mixture Collector Figure 2 Diffuser Figure 3...
Страница 194: ...1 Plate 2 Spring 3 Plate 4 Gear 5 Accessory Drive Shaft Blower Coupling Figure 4...
Страница 204: ...Oil Sump Figure 4...
Страница 216: ...Engine M 14P Gear Train Figure 1...
Страница 247: ...Carburetor AK 14P Operation Diagram Figure 1...
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Страница 267: ...OPERATIONS AND TECHNICAL REQUIREMENTS CORRECTIVE ACTIONS CH ECKED BY Carburetor AK 14P Right Side View Figure 201...
Страница 273: ...Carburetor Altitude Control Needle Position Versus Barometric Pressure Barometric Graph Figure 203...
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Страница 288: ...T t en 0 CO 0 T K D fi h0 Ol f 01 3 0 F4...
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Страница 309: ...SPARK PLUG SD 49SMM MAINTENANCE PRACTICES 1 LIST OF TASK CARDS Title Task Card Uo Removal 201 Installation 202...
Страница 344: ...Generator Electrical Connection Diagram Commutator Side View Figure 3 1 Main Pole 2 Interpole...
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