Table of Contents
- 1 Why does a compressor of an aircraft engine has more number of stages compared to a turbine section?
- 2 Why are there multiple stages of compression in an axial flow compressor?
- 3 Why do compressor stages get smaller?
- 4 Why do compressor blades get progressively shorter along the length of an axial flow compressor?
Why does a compressor of an aircraft engine has more number of stages compared to a turbine section?
They partially convert high velocity air into high pressure. Each consecutive compressor stage compresses the air even more. The number of stages is determined by the amount of air and total pressure rise required. The greater the number of stages, the higher the compression ratio.
Why are there multiple stages of compression in an axial flow compressor?
An axial-flow compressor compresses its working fluid by first accelerating the fluid and then diffusing it to obtain a pressure increase. By producing low-pressure increases of the order of 1.1:1–1.4:1, very high efficiencies can be obtained. The use of multiple stages permits overall pressure increases up to 40:1.
Why are compressor ratios less than turbine ratios?
The decrease in power results in a decrease in the compressor pressure ratio and thus a decrease in the turbine pressure ratio. If operation is at a constant EGT at lower power as discussed above, the turbine entry temperature and the combustion temperature decrease as the compressor pressure ratio decreases.
How many stages does a compressor have?
Modern engines can use 10-15 compressor stages. Advantages of the axial compressor are its higher flow rate and greater pressure ratio, which results in higher thrust and fuel efficiency.
Why do compressor stages get smaller?
In the axial compressor the air flows parallel to the axis of rotation. Through the compressor, the flow area decreases and the blades get smaller and smaller from stage to stage and this compensates for the increase of air pressure and density, creating a constant axial velocity.
Why do compressor blades get progressively shorter along the length of an axial flow compressor?
As indicated earlier in figure 3, the length of the blades, and the annulus area, this is the area between the shaft and shroud, decreases throughout the length of the compressor. This reduction in flow area compensates for the increase in fluid density as it is compressed, permitting a constant axial velocity.
What is the difference between compressor stall and compressor surge?
Compressor surge Rotating stall can morph into the extreme case of a compressor performance failure called surge. In the words of compressor expert Ivor Day, stall is a disturbance of compressor flow in the tangential direction, while surge is a disturbance in the axial direction.