Altitude Ignition/Lean Decel Study.
Abstract
The objective of this study was to develop analytical tasks consisting of new or improved models for predicting altitude ignition and lean deceleration blowout. The approach taken was to describe the ignition and flame stabilization limits in terms of characteristic 'time' models. Characteristic times associated with chemical kinetics, fuel evaporation and hot flow residence are quantified for ignition and lean deceleration blowout limits. These expressions were interrelated according to the criteria for successful ignition and flame stabilization. Statistical analysis was used to compare the various expressions and select the appropriate terms that formulate models which best fit the data for altitude ignition and lean deceleration blowout. The models linearly correlate variations in combustor pressure, inlet temperature, fuel-air ratio, fuel temperature, air velocity, pressure drop, combustor front end geometry and injector size using existing data from USAF, Navy, NASA and P&W sponsored programs on operability performance of military and commercial gas turbine combustors. These models have been based entirely on full scale engine test. Keywords: Mathematical predictions: Ignition; Lean deceleration blowout; Characteristic times; Fuel evaporation time; Chemical reaction; Spark kernel quenching; Hot flow residence time.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1985
- Accession Number
- ADA163052
Entities
People
- Dean Andreadis
Organizations
- Pratt & Whitney