摘要：

The phase/Doppler interferometry technique is applied to make spatially-resolved measurements of liquid oxygen (LOX) drop size and drop velocity in a combusting oxygen/hydrogen spray flowfield produced by a swirl coaxial rocket injector. The experiment is performed in a single-element optically accessible rocket combustion chamber at elevated pressure and temperature conditions for an oxidizer to fuel mass flow ratio of 30. Using the present effort as an example, the challenges of obtaining and interpreting measurements in representative rocket combustion environments are discussed. Issues relating to the application of the drop measurement technique for interrogating high density, high flowrate rocket injector sprays are highlighted.

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