M15c4

22問 • 9ヶ月前

ユーザ名非公開

通報

問題一覧

The centrifugal compressor is ideally suited to

reverse flow turboprop engines

double entry compressor problem is

difficulty in designing

centrifugal compressor Advantage

Simple ,Low weight & cost and High pressure rise per stage

centrifugal compressor Disadvantage

Large frontal area and limited number of stages

Compressor stage

is a raw of rotor and a raw of stator

Stator

increase pressure and control the direction of airflow.

Rotor

increase air velocity

Compressor blades and diameter getting smaller (front to rear) to maintain

axial velocity through the compressor

Compressor pressure ratio

is the ratio between compressor outlet pressure to compressor inlet pressure.

The primary factor that control the pressure ratio

is number of stages in the compressor.

The highest gas pressure through gas turbine engine at

compressor outlet

Root

is lowest stagger angle at the root.

Compressor RPM is limited by

blade tip speed.

To calculate compressor outlet pressure you need to

multiply inlet pressure with compression ratio

A combination type (Hybrid compressor) used in

small gas turbine engines with reverse flow combustion.

Engine design point is the point which engine will operate during most of its service

it is based on cruise speed and altitude (air density).

Twin spool compressor is more

flexibility of operation and greater resistance to surge

Low pressure compressor runs at

lower RPM than high pressure compressor

Single spool compressor is

less efficient

Variable stator vanes and bleed valve used to

avoid surge

In a centrifugal flow compressor the high efficiency of compressor achieved by

keeping clearance between the impeller and casing As small as possible to preventing excessive air leakage

The function of snubber mid span shroud used on fan blade

to support fan blade and prevent aerodynamic instability

mod5 training

mod5 training

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問題一覧

The centrifugal compressor is ideally suited to

reverse flow turboprop engines

double entry compressor problem is

difficulty in designing

centrifugal compressor Advantage

Simple ,Low weight & cost and High pressure rise per stage

centrifugal compressor Disadvantage

Large frontal area and limited number of stages

Compressor stage

is a raw of rotor and a raw of stator

Stator

increase pressure and control the direction of airflow.

Rotor

increase air velocity

Compressor blades and diameter getting smaller (front to rear) to maintain

axial velocity through the compressor

Compressor pressure ratio

is the ratio between compressor outlet pressure to compressor inlet pressure.

The primary factor that control the pressure ratio

is number of stages in the compressor.

The highest gas pressure through gas turbine engine at

compressor outlet

Root

is lowest stagger angle at the root.

Compressor RPM is limited by

blade tip speed.

To calculate compressor outlet pressure you need to

multiply inlet pressure with compression ratio

A combination type (Hybrid compressor) used in

small gas turbine engines with reverse flow combustion.

Engine design point is the point which engine will operate during most of its service

it is based on cruise speed and altitude (air density).

Twin spool compressor is more

flexibility of operation and greater resistance to surge

Low pressure compressor runs at

lower RPM than high pressure compressor

Single spool compressor is

less efficient

Variable stator vanes and bleed valve used to

avoid surge

In a centrifugal flow compressor the high efficiency of compressor achieved by

keeping clearance between the impeller and casing As small as possible to preventing excessive air leakage

The function of snubber mid span shroud used on fan blade

to support fan blade and prevent aerodynamic instability