Combustion in Advanced Gas Turbine Systems. Proceedings of by I. E. Smith

By I. E. Smith

Show description

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

Modern Missile Guidance

Книга sleek Missile suggestions smooth Missile GuidanceКниги Наука. Техника Автор: Rafael Yanushevsky Год издания: 2007 Формат: pdf Издат. :CRC Страниц: 240 Размер: 2,7 ISBN: 1420062263 Язык: Английский0 (голосов: zero) Оценка:Written via knowledgeable with greater than 30 years of expertise, smooth Missile advice includes new analytical effects, bought by means of the writer, that may be used for research and layout of missile counsel and keep watch over platforms.

A Review of NASA's 'Atmospheric Effects of Stratospheric Aircraft' Project

The NRC Panel at the Atmospheric results of Aviation (PAEAN) used to be validated to supply information to NASA's Atmospheric results of Aviation application (AEAP) by means of comparing the appropriateness of the program's learn plan, appraising the project-sponsored effects relative to the present nation of medical wisdom, determining key medical uncertainties, and suggesting study actions prone to lessen these uncertainties.

Extra resources for Combustion in Advanced Gas Turbine Systems. Proceedings of an International Propulsion Symposium Held at the College of Aeronautics, Cranfield, April 1967

Sample text

Decomposes at about 460°C. Thus, since in practice most fuel oil ashes contain both sodium and vanadium, it would appear that the combined use of magnesium and kaolin might be effective against both corrosion and deposition. 8V205). 7V205 has been reported;(^^) this study also illustrates the effectiveness of magnesium and kaolin on the melting points of fuel oil ashes, as shown in Table 2. TABLE 2. 5/1/0-5 615 1140 1060 — 950 710 >1250 >1250 >1250 1220 72%^,V205 No sodium 32 W. (^°> When operating a gas turbine on a distillate fuel oxidation of the blading occurs in a fairly uniform manner over the whole of the surface exposed to the gas stream.

14 indicates the thermal efficiencies obtainable from such a reheat cycle. Such a system would be simpler c CCi >; S e e figure II for s y m b o l s except T2 = reheat turbine T, CC2 25 4 6 Compression ratio FIG. 14. Thermal efficiency of high temperature gas turbine with reheat. to operate than those with intermediate cooling, but the first cost might be appreciably higher due to the use of two turbines with cooled blading. If a conventional heat exchanger is introduced into this cycle, with the pre­ heat temperature again limited to 500°C, then the thermal efficiency can again COMBUSTION IN INDUSTRIAL GAS TURBINES 41 be advanced.

U. is approximately equivalent to 1 microgram/litre for the range of size of soot particles which we experience) represents an acceptable level of exhaust emission for a moving source such as an aircraft. Making allowance for the dilution 60 κ . G R A D O N A N D S . C. u. at combustion chamber exit. u. An examination of several flame tubes to the revised standard which had smoke levels considerably above the average value indicated that the depth of plunging of the secondary holes had a marked effect on the exhaust emission as seen in Fig.

Download PDF sample

Rated 4.91 of 5 – based on 42 votes