1st Review Flashcards
DIVERGENT Duct. What is it’s shape & purpose? (static & dynamic press, velocity)
VELOCITY OF AIR DECREASES
EXPANDS IN DIAMETER
STATIC PRESSURE INCREASES
TEMP OF AIR INCREASES
What is a Convergent duct’s shape & what does it do?
INCREASES VELOCITY OF AIR
DECREASES IN DIAMETER
DECREASES STATIC PRESSURE
TEMP OF AIR DECREASES
Define Bernoulli’s Principle
THE SUM of the DYNAMIC & STATIC PRESSURES
WILL ALWAYS BE EQUAL
Define the Brayton Cycle.
Often referred to as the CONSTANT PRESSURE CYCLE.
Turbine eng 4 events to support combustion occur constantly & simultaneously:
They are:
Intake
Compression
Ignition/Power
Exhaust
What is meant by the term ‘twin’ spool?
Two rotors, one LP, one HP (N1 and N2)
What is EPR’s application for a turbine engine?
- Engine pressure ratio
- Outlet Pressure/Inlet Pressure
- To determine engine thrust
Define N1 (in a 2-spool engine)?
Low Pressure spool
Define N2 (in a 2-spool engine)?
High Pressure Spool
List the 5 primary areas within a turbine engine, front to back.
Intake, Compressor, Combustion chambers, Turbine, exhaust
What is a turboprop engine?
Configuration where turbine engine drives propeller
Describe an axial Compressor stage, how does it work?
Increases the static pressure from the inlet duct and directs
it to the combustion chamber (thru diffuser) at the correct
pressure (potential energy), velocity and temp
The Rotor and Stator vanes create divergent ducts
1 complete COMP Stage is
: A ROTOR followed by a STATOR.
Describe an axial TURBINE stage, how does it work?
The purpose of the TURBINE section is to convert the kinetic (velocity) and heat energy of the combustion gases into mechanical energy to rotate the Turbine to drive the fan/propeller/compressors/accessories. The Turbine section is located downstream of the combustion section.
1 complete TURBINE Stage is defined as
: A STATOR followed by a ROTOR
Bleed Air: What is it? Uses? Sources?
BLEED AIR IS A SOURCE of AIR PRESSURE (Pneumatic press) FROM THE COMPRESSOR THAT IS USED FOR VARIOUS FUNCTIONS.
TYPICAL USES ARE:
CABIN PRESS
STARTING
ANTI-ICING SYSTEMS
What is a compressor stall?
a compressor stall occurs when the blade angle of attack exceeds the critical angle of attack, caused by an imbalance between the inlet velocity and rpm
label the pt6 sections 8,9,10
8: Exhaust Outlet
9: Reduction Gearbox
10: Propeller Drive Shaft
Label 3,4,5
3: Centrifugal Compressor
4: Igniter
5: Fuel Nozzle
Label 7,6,2
7: Free(Power) Turbine
6: Compressor Turbine
2: Three stage Axial flow compressor
Label 1, 11
1: Air inlet
11: Accessory Gearbox
