Pulse combustion heat exchanger system and method

An aerovalve (A), having an aerovalve longitudinal axis (X1), an outer surface (S) with an outer diameter (D0), an interior (A-IN), a rear end (1E1) having a rearwardly facing rear surface (1E1S), a forward end (2E1) having a forwardly facing forward surface (2E1S), and a total aerovalve length (L) defined between the rear and forward ends (1E1, 2E1) along the aerovalve longitudinal axis (X1), the aerovalve (A) further comprising:

• an oxidant inlet (1A0) located at the rear end (1E1), the oxidant inlet (1A0) configured to introduce oxidant (1A1) into the interior (A-IN) of the aerovalve (A);
• an oxidant and fuel mixture outlet (2A0) located at the forward end (2E1), the oxidant and fuel mixture outlet (2A0) configured to expel an oxidant and fuel mixture (1A3) present in the interior (A-IN) of the aerovalve (A);
• a first plurality of fuel inlet ports (1A, 1B, 1C, . . . ) opening to the outer surface (S), a second plurality of fuel outlet ports (2A, 2B, 2C, . . . ) opening to the interior (A-IN), and a third plurality of fuel transfer channels (3A, 3B, 3C, . . . ) configured to transfer fuel (1A2) from the first plurality of fuel inlet ports (1A, 1B, 1C, . . . ) to the second plurality of fuel outlet ports (2A, 2B, 2C, . . . );
• a first inner conical surface (S1) tapering radially inwardly at a first angle (A1) to a first inner diameter (D1), the first inner conical surface (S1) extending in the forward direction from proximate the rear end (1E1) for a first length (L1) along the aerovalve longitudinal axis (X1);
• a second inner conical surface (S2) expanding radially outwardly at a second angle (A2) to a second inner diameter (D2), the second inner conical surface (S2) extending in the forward direction from proximate the first inner conical surface (S1) for a second length (L2) along the aerovalve longitudinal axis (X1), the second inner diameter (D2) being less than the outer diameter (D0);
• and
• a third inner conical surface (S3) expanding radially outwardly at a third angle (A3) to a third inner diameter (D3), the third inner conical surface (S3) extending in the forward direction from proximate the second inner conical surface (S2) for a third length (L3) along the aerovalve longitudinal axis (X1), the third inner diameter (D3) being greater than the first and second inner diameters (D1, D2) and less than the outer diameter (D0);
• wherein:
• the first angle (A1) is greater than the second angle (A2);
• the third angle (A3) is greater than the second angle (A2);
• and
• the second plurality of fuel outlet ports (2A, 2B, 2C, . . . ) are positioned on the third inner conical surface (S3).