Date of Award

4-2014

Document Type

Thesis - Open Access

Degree Name

Master of Science in Aerospace Engineering

Department

Aerospace Engineering

Committee Chair

Sandra Boetcher, Ph.D.

First Committee Member

Lakshmanan L. Narayanaswami, Ph.D.

Second Committee Member

Eric R. Perrell, Ph.D.

Abstract

The following work investigates an alternative supersonic film cooling method for hydrogen-fueled, gas-generator cycle rocket engines. The research is intended to serve as an initial proof-of-concept for a biased supersonic film cooling method envisioned for nozzle extension thermal management. The proposed method utilizes a dual-stream injection process that leverages the high heat capacity of the fuel-rich gas-generator gases. By comparing the proposed cooling strategy to the conventional mixed injection process, the research numerically validates the biased supersonic film cooling scheme for low supersonic slot Mach numbers. The average film cooling effectiveness was improved 5%-8% with increases as high as 12%. The average reduction in wall temperature ranged from 9%-15% with maximum reductions as high as 36% over the conventional method.

Share

COinS