Accession Number:

AD0007463

Title:

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

Descriptive Note:

Corporate Author:

AERONAUTICAL SYSTEMS DIV WRIGHT-PATTERSON AFB OH DIRECTORATE OF WEAPON SYSTEMS OPERATIONS

Personal Author(s):

Report Date:

1952-11-01

Pagination or Media Count:

61.0

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.

Subject Categories:

  • Reciprocating and Rotating Engines
  • Air Conditioning, Heating, Lighting and Ventilating

Distribution Statement:

APPROVED FOR PUBLIC RELEASE