US 3,937,189 A · Fan shroud exit structure

Abstract

A heat exchanger apparatus for a liquid-cooled internal combustion engine including a radiator axially spaced from the engine, an engine driven, suction type fan axially spaced intermediate the engine and radiator for drawing cooling air axially through the radiator, and fan shroud means shaped and positioned with respect to the radiator and the blades of the fan whereby the major component of the air stream discharged by the fan is in a direction reversed to the direction to the major component of the air stream entering the radiator. The fan shroud structure is formed to provide a generally cylindrical exit throat section (CF), a radial flat discharge section (RF), and a radial expander or diverging section (R) serving as a transition between the throat section and the radial exit section and wherein the propeller-type blades of the fan have a projected axial width (AW). The various shroud structure sections are dimensioned with respect to such projected axial width (AW) of the fan blades and the fan blades are positioned with respect to such shroud structure sections in the following manner: CF = AW/3, RF = AW/3, R = 2AW/3, and the radial plane containing the trailing edges of the fan blades is axially spaced outwardly from the radial plane containing the radial exit section (RF) a distance X.sub.E and wherein the magnitude of X.sub.E is between 60 and 75 percent of the projected axial width (AW) of the fan blades.

Claims5

Dependent claims

A heat exchange apparatus comprising:

a heat exchange means having front and rear faces;
shroud means operatively connected to said heat exchange means about its rear face, said shroud means including a rearwardly extending exit shroud means comprising a radially outwardly and axially rearwardly extending curved shroud section and a flat portion extending radially outwardly from one end of said curved section;
an axial flow, suction-type fan having a plurality of fan blades, each of said fan blades having a trailing edge and a leading edge, said leading edges lying generally in a first radial plane and said trailing edges lying generally in a second radial plane axially spaced rearwardly from said first radial plane a distance AW and wherein the following relationship within plus or minus 12 percent of AW exists:
RR = AW/3 where RF is the radial length of said radially extending shroud flat portion and R = 2AW/3 where R is the radius of curvature of said curved shroud section;
and said second radial plane being axially spaced rearwardly from the radial plane containing said radially extending shroud flat portion a predetermined distance (X.sub.E) having a value of more than 50 but less than 100 percent of said axial distance AW.

2 more elements

In a cooling system for an internal combustion engine, the combination, comprising:

a liquid-cooled internal combustion engine;
a generally upright radiator axially spaced forwardly of said engine having front and rear faces;
means for circulating a liquid coolant between said radiator and said engine;
shroud means extending generally rearwardly and axially from said radiator including an entrance shroud means having forwardmost edge means operatively connected to said radiator about its rear face and an exit shroud means extending rearwardly from said entrance shroud means, said exit shroud means comprising a generally cylindrical throat section having a forwardmost edge means joined to a rearwardmost edge means of said entrance shroud means, a radially outwardly and axially rearwardly extending curved shroud section operatively connected to the rearwardmost end of said throat section and a flat portion extending radially outwardly from the rearwardmost end of said curved shroud section;
an axial flow, suction-type fan axially spaced intermediate and said radiator and engine, and driven by said engine, said fan having a plurality of fan blades, each of said fan blades having a trailing edge and a leading edge, said leading edges lying substantially at a first radial plane and said trailing edges lying generally in a second radial plane axially spaced rearwardly from said first radial plane a distance AW, and said second radial plane being axially spaced rearwardly from the radial plane containing said radially extending shroud flat portion of predetermined distance (X.sub.E), said predetermined distance (X.sub.E) having a value of at least 55 percent of said axial distance AW, and wherein the following relationships within plus or minus 12 percent of AW exists:
R = 2AW/3, CF = AW/3, and RF = AW/3 where R is the radius of curvature of the curved shroud section;
CF is the axial length of the shroud throat section, and RF is the radial length of the radially extending shroud flat portion.

4 more elements

Dependencies are inferred from the claim text.

Fan shroud exit structure

Life of this patent

Fan shroud exit structure

Life of this patent

Abstract

Claims5