Pylon Fuel Injector Design for a Scramjet Combustor (Postprint)
Abstract
This paper covers the initial development of an in-stream fuel injector concept for a circular hydrocarbon scramjet combustor. Three scramjet fuel injection pylon configurations are established--a basic pylon, a ramp pylon, and an alternating wedge pylon. The first pylon configuration is a baseline. The latter two configurations introduce streamwise vorticity into the flow to increase mixing action. Operating conditions and design considerations are discussed and the fuel injector configurations are presented. A testing methodology relating flight conditions to cold flow conditions is addressed. Initial Computational Fluid Dynamic simulations without fuel injection are presented for a wind tunnel cold flow test point. Two parameters used for comparison among the pylons are axial vorticity generation and total pressure loss. It is found the ramp and alternating wedge pylons increase streamwise vorticity in the flow over the basic pylon. The alternating wedge pylon increases streamwise vorticity the most. It is also found the ramp and alternating wedge pylons result in slightly increased total pressure losses due to the induced streamwise vorticity.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 2007
- Accession Number
- ADA486757
Entities
People
- Jason C. Doster
- Mark R. Gruber
- Paul I. King
- Raymond C. Maple
Organizations
- Air Force Research Laboratory