By I. E. Smith
Read Online or Download Combustion in Advanced Gas Turbine Systems. Proceedings of an International Propulsion Symposium Held at the College of Aeronautics, Cranfield, April 1967 PDF
Similar aeronautics & astronautics books
There's expanding curiosity within the capability of UAV (Unmanned Aerial car) and MAV (Micro Air motor vehicle) expertise and their large ranging functions together with defence missions, reconnaissance and surveillance, border patrol, catastrophe quarter evaluation and atmospheric study. excessive funding degrees from the army zone globally is using learn and improvement and lengthening the viability of self sufficient systems as replacements for the remotely piloted automobiles most of the time in use.
This e-book deals a basic review of the physics, thoughts, theories, and versions underlying the self-discipline of aerodynamics. a specific concentration is the means of pace box illustration and modeling through resource and vorticity fields and through their sheet, filament, or point-singularity idealizations.
- Aircraft Fuel Systems
- Electrogravitics Systems: Reports on a New Propulsion Methodology
- Fluid dynamics
- Basic Aerodynamics: Incompressible Flow
Additional resources for Combustion in Advanced Gas Turbine Systems. Proceedings of an International Propulsion Symposium Held at the College of Aeronautics, Cranfield, April 1967
18. Whilst this standard of flame tube gave satisfactory smoke performance, occasional rig tests would produce a gas temperature traverse with peak temperatures as much as 100° above the normal. It was felt that this problem would be largely alleviated and, in all probability, the smoke emission would be still further reduced if, whilst generally retaining the overall flow proportions of the larger chuted secondary holes flame tube, the overall pressure loss could be restored to the original design value by reducing all the hole areas in the flame tube.
48 κ . G R A D O N A N D S . C. M I L L E R FIG. 4. Flame tube cooling devices. FIG. 5. Tubo-annular dilution zone. THE ROLLS-ROYCE S P E Y 49 ENGINE Also from the Conway came the pilot nozzle spray-bar configuration on the fuel burner known as the microcage which was added to the basic duple burner to give consistent ignition (see Fig. 7). Lack of consistent ignition had been shown to be a serious problem soon after the Conway entered service and the microcage design, which produced a solution by reducing fuel concentration near the igniter, was incorporated quickly into the Spey.
F r o m that engine came the principles of flame tube cooling—the hemispherical flare and the discharge nozzle by splash cooling strips, and the body of the flame tube by wigglestrips (see Fig. 4). Further, Avon work had demonstrated the necessity for a sphtter and back stop system in the annulus to control the difficult dilution airflow problems on a tubo-annular design (see Fig. 5). From the Conway came the idea of the common entry snout to give a uniform annulus velocity distribution. In any tubo-annular system, the airflow is reluctant to spread evenly round the circumference of the flame tube and low velocity regions appear at the top and bottom (see Fig.