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15.3 INLET




 http://part66.blogspot.com/
INLET PURPOSE
• To provide stream line air and to prevent air
  speed going to compressor above Mach 1
  (supersonic speed)
• To prevent from shock wave, compressor cant
  work and damage might occurs.
SUBSONIC TYPE INLET
         Aircraft speed can up to Mach 1.2

             CONVERGEN TYPE INLET            BELLMOUTH INLET (HELICOPTER)




Convergen duct




             Mach 1      M< 1
SAND AND ICE SEPERATOR
       TURBOPROP INLET




                  Sand stay at bottom due to inertia
SUPERSONIC TYPE INLET
                  Aircraft speed can up to Mach 4

VARIABLE THROAT AREA INLET                     MOVABLE PLUG TYPE
ICE PROTECTION
• Ice tend to make the airflow not smooth.
• Can cause engine un efficient due to turbulent
  and compressor stall.
• Normally occur on intake lip and compressor
  inlet ducting.
TYPE OF ICE PROTECTION
• Hot Air System
   – Bleed from HP compressor and pass through pressure regulating valve
   – Provide overheat sensor to prevent overheated

• Electrical System
   – Normally on turboprobeller
   – Electrical heating element bounded to outer surface of intake cowl
   – Intake leading edge continously heated (anti-icing) and other strip
     heted intermittent (de-icing)

• Hot Oil System
   – Utilise hot scavenge oil to heat inlet casing
   – Normally in conjuction with hot air anti-icing or electrical system

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EASA Part 66 Module 15.3 : Inlet

  • 2. INLET PURPOSE • To provide stream line air and to prevent air speed going to compressor above Mach 1 (supersonic speed) • To prevent from shock wave, compressor cant work and damage might occurs.
  • 3. SUBSONIC TYPE INLET Aircraft speed can up to Mach 1.2 CONVERGEN TYPE INLET BELLMOUTH INLET (HELICOPTER) Convergen duct Mach 1 M< 1
  • 4. SAND AND ICE SEPERATOR TURBOPROP INLET Sand stay at bottom due to inertia
  • 5. SUPERSONIC TYPE INLET Aircraft speed can up to Mach 4 VARIABLE THROAT AREA INLET MOVABLE PLUG TYPE
  • 6. ICE PROTECTION • Ice tend to make the airflow not smooth. • Can cause engine un efficient due to turbulent and compressor stall. • Normally occur on intake lip and compressor inlet ducting.
  • 7. TYPE OF ICE PROTECTION • Hot Air System – Bleed from HP compressor and pass through pressure regulating valve – Provide overheat sensor to prevent overheated • Electrical System – Normally on turboprobeller – Electrical heating element bounded to outer surface of intake cowl – Intake leading edge continously heated (anti-icing) and other strip heted intermittent (de-icing) • Hot Oil System – Utilise hot scavenge oil to heat inlet casing – Normally in conjuction with hot air anti-icing or electrical system