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EASA Part 66 Module 15.3 : Inlet

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EASA Part 66 Module 15.3 : Inlet

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  1. 1. 15.3 INLET http://part66.blogspot.com/
  2. 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. 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. 4. SAND AND ICE SEPERATOR TURBOPROP INLET Sand stay at bottom due to inertia
  5. 5. SUPERSONIC TYPE INLET Aircraft speed can up to Mach 4 VARIABLE THROAT AREA INLET MOVABLE PLUG TYPE
  6. 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. 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
  1. 1. 15.3 INLET http://part66.blogspot.com/
  2. 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. 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. 4. SAND AND ICE SEPERATOR TURBOPROP INLET Sand stay at bottom due to inertia
  5. 5. SUPERSONIC TYPE INLET Aircraft speed can up to Mach 4 VARIABLE THROAT AREA INLET MOVABLE PLUG TYPE
  6. 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. 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

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