DESIGN EQUATIONS FOR THE INTERWARMER INDUCTION AIR HEATING SYSTEM FOR RECIPROCATING AIRCRAFT ENGINES

Abstract

The heating system is a development of the exhaust-manifold and accessory-section types. Hot air is ducted from around the exhaust manifold over heat the induction air. The hot air flow is controlled by a valve in the duct on the inlet side of the heat exchanger and is induced and regulated by airstream venturi action on a flap facing rearward on the duct outlet side. Flight-test data from B-29 R-3350-57 engines and test-stand data from a similar engine were utilized to develop empirical equations defining the temperature and flow conditions in the interwarmer and contributing exhaust and induction systems. The equations are considered suitable for determining a reciprocating-engine interwarmer system in which a carburetor air temperature of 0 deg F is provided at -65 deg F.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1952
Accession Number
AD0007463

Entities

People

  • Edward C. Theiss

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Flow
  • Air Force
  • Air Force Facilities
  • Aircraft Engines
  • Energy
  • Equations
  • Exhaust Systems
  • Flow
  • Heat Loss
  • Heat Transfer
  • Low Temperature
  • Measurement
  • Plastic Explosives
  • Reciprocating Engines
  • Sea Level
  • Static Pressure
  • Test Stands

Readers

  • Aerospace Engineering
  • Internal Combustion Engine (ICE) Technology.
  • Thermal Physics or Thermal Science.