Restricted Acoustic Modal Analysis Applied to Internal Combustor Spectra and Cross-Spectra Measurements

By: Administration (Nasa), National Aeronaut

A treatment of the modal decomposition of the pressure field in a combustor as determined by two Kulite pressure measurements is developed herein. It is applied to a Pratt & Whitney PW4098 engine combustor over a range of operating conditions. For modes other than the plane wave the new part of the treatment is the assumption that there are distinct frequency bands in which the individual modes, including the plane wave mode, overlap such that if circumferential mode m and circumferential mode m-1 are present than circumferential mode m 2 is not. Consequently, in the analysis used herein at frequencies above the first cut-off mode frequency, only pairs of circumferential modes are individually present at each frequency. Consequently, this is a restricted modal analysis. A new result is that the successful use of the same modal span frequencies over a range of operating conditions for this particular engine suggests that the temperature, T, and the velocity, v, of the flow at each operating condition are related by c(sup 2)-v(sup 2) = a constant where c is the speed of sound. Miles, Jeffrey Hilton Glenn Research Center NASA/TM-2006-214351, E-15626, AIAA Paper 2006-2581 WBS 581-02-08-03 COMBUSTION CHAMBERS; ACOUSTIC VELOCITY; ACOUSTIC MEASUREMENT; PRESSURE MEASUREMENT; PRESSURE DISTRIBUTION; PLANE WAVES; DECOMPOSITION; FREQUENCIES; SIGNAL ANALYZERS

• Format: Paperback
• Language: English
• ISBN: B08F6MVHQ2
• ISBN13: 9798672764962
• Release Date: January 1
• Publisher: Independently Published
• Length: 34 Pages
• Weight: 0.23 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"