72 Powerplant Flashcards
How is fuel injected into the combustion chamber liner?
14 simplex nozzles consisting of primary and secondary transfer tubes.
What happens to the direction of the air as it enters the combustion liners?
changes direction 180 degree’s
What is the purpose of the stator vanes located between each stage of compression.
Diffuses the air, raises its static pressure and directs it to the. next stage.
The engine utilizes 2 independent turbine sections what are they?
One drives the compressor in the gas generator section, the second (two stage power turbine) driving the prop shaft.
What is contained inside the RGB?
two-stage planetary gear-train, accessory drives, torque-meter and prop shaft.
Where is the RGB located on the engine?
Front of the engine consisting of 2 allow housings bolted together at Flange A
1st stage ring gear, is allowed to move axially for what purpose?
Torquemeter application.
How are the 2 stages of planetary gears connected?
Flexible coupling which acts to dampen any vibrations.
What is the second stage carrier splined together with?
The prop shaft, a flanged roller bearing supports the 2 units (prop shaft and second stage carrier)
How are hydraulic locks prevented for the torquemeter chamber?
Continuous bleed of oil through the small bleed orifice at the top of the torque-meter cylinder.
What is housed inside the inlet case.
No.1 Bearing, oil level guage.
Where is P2.5 air taken from for airframe services?
12 oclock position on the gas generator cas.
Where is P3 air taken from?
9 oclock position between the engine mounts.
Torque from the power turbine section is transmitted through the power turbine shaft and turbine coupling to
the first-stage sun gear.
The first-stage of the reduction geartrain consists of
three planet gear assemblies in a rotating carrier balancing assembly and a non
rotating ring gear.
The second-stage sun gear drives
five planet gears mounted in the second-stage carrier.
The accessories located on the front housing are driven by
a bevel drive gear mounted at the rear of the propeller shaft thrust bearing
assembly.
Propeller thrust loads are absorbed by
the ball bearing assembly, located on the front section of the propeller shaft.
What flanges are incorporated for your compressor inlet case? on?
Flange F (fwd, gas gen case) Flange G(aft, agb)
Housed in the inlet case is the
No. 1 bearing assembly with its associated rotor and stator seals and the No. 1 bearing oil jet.
The center fireseal mount ring, which forms a bulkhead between the
compressor air inlet zone and the front of the engine
The rear fireseal mount ring, which forms a bulkhead between the
compressor air inlet zone and the accessory gearbox
A bleed air adapter, located at the 12 o’clock position on the case, provides
P2.5 air for
airframe services.
P3 airframe air is provided by an adapter located at the
9 o’clock position between the main engine mounts
The compressor rotor is supported on a
No. 1 ball bearing and a No. 2 roller bearing assembly.
