Simulation of Compressor Performance Deterioration due to Erosion

Experimental results obtained from cascades and one stage compressor performance tests before and after erosion were used to test a fault model to represent erosion. This model was implemented on a stage stacking program developed to demonstrate the effect of erosion in a multistage compressor. The effect of the individual stage erosion on the overall compressor performance is also demonstrated.

Influence of Fuel Chemical Properties on Soot Emissions From Gas Turbine Combustors

The influence of fuel composition on soot emissions from continuous flow combustors is examined. A study of the combustion characteristics of a wide range of present and potential aviation fuels suggests that smoke point provides a better indication of sooting tendency than does hydrogen content. It is concluded from this study that the best empirical relationship between fuel chemical composition and soot emissions is one which combines two fuel composition parameters — smoke point and naphthalene content — into a single parameter which is shown to correlate successfully soot emissions data acquired from several different fuels burning in a variety of gas turbine and model combustors.

Physical Aspects of Deposition From Coal Water Fuels Under Gas Turbine Conditions

Deposition, erosion, and corrosion (DEC) experiments were conducted using three coal-water fuels (CWF) in a staged subscale turbine combustor operated at conditions of a recuperated turbine. This rich-quench-lean (RQL) combustor appears promising for reducing NOx levels to acceptable levels for future turbines operating with CWF. Specimens were exposed in two test sections to the combustion products from the RQL combustor. The gas and most surface temperatures in the first and second test sections represented temperatures in the first stators and rotors, respectively, of a recuperated turbine. The test results indicate deposition is affected substantially by gas temperature, surface temperature, and unburned carbon due to incomplete combustion. The high rates of deposition observed at first stator conditions showed the need for additional tests to identify CWF coals with lower deposition tendencies and to explore deposition control measures such as hot gas cleanup.

Experimental Investigations of Pressure Drop in the Combustion Chamber of Gas Turbine

In bibliography we can find many methods of determining pressure drop in the combustion chambers of gas turbines, but there is only very few data of experimental results. This article presents the experimental investigations of pressure drop in the combustion chamber over a wide range of part-load performances (from minimal power up to take-off power). Our research was carried out on an aircraft gas turbine of small output. The experimental results have proved that relative pressure drop changes with respect to fuel flow over the whole range of operating conditions. The results were then compared with theoretical methods.

Explosions in Gas Turbine Lube Oil Reservoir Result in Installation of Dry Gas Seal System

Mechanical dry gas seal systems were retrofitted into two centrifugal natural gas compressors which are located offshore in the Norwegian sector of the North Sea. The project was initiated after a fire and several gas explosions had occurred in the gas turbine lube oil reservoir. These incidents were a result of gas leaking from the compressor’s seal oil system and then migrating via the lube oil lines into the reservoir. The dry gas seal systems have eliminated gas leakage into the turbine lube oil reservoir, eliminating the hazard of gas explosion. The retrofits have also provided additional benefits including reductions in space and weight, reduced power usage, reduced maintenance, and elimination of seal oil consumption which had been up to 440 gal./day (2000 liters/day).

The Effects of Inerts on Emissions and Performance of an Industrial Engine

Gaseous fuels such as landfill gas contain significant quantities of inerts, typically CO2 and N2. This can lead to difficulties in predicting the emission and thermodynamic performance of industrial gas turbines. An algorithm has been developed to predict emissions of NOx for known quantities of inerts and effects on performance quantified. The effect of steam injection is compared to that of inerts and a relationship established.

The Design and Performance of a Reverse Flow Combustion System for the TP 500 Gas Turbine Engine

The TP 500 is a 525 SHP turboprop engine being produced by Teledyne Continental Motors for general aviation use. This paper describes the design and performance of the reverse flow fan spray combustion system being supplied for this engine. The main features of the design are described in some detail, together with the performance of the system as established in the combustion test facility at AIT Ltd and covering light-up to Take-Off conditions and sea level to 6km altitude.

The Effects of Hydrocarbon Fuels Upon Exhaust Pollutants in Gas Turbine Combustors

More than 100 different fuels have been examined for the influence of their properties on pollutant levels, using two different combustors. Comparison with data from other sources is attempted. Some simple correlations are suggested.

Experimental Study of a Reverse Flow Combustor: Influence of Primary Holes on Combustor Efficiency

The primary zone of the reverse flow combustors for helicopters tested at ONERA is fed with air from primary holes, multiples holes for the wall cooling and prevaporiser tubes. The effect of the primary holes on the combustor performances has been studied. Gas sampling inside the combustor has been achieved in order to understand the flow mechanisms with and without primary holes. The differences observed on the 2 configurations are not significant. Air from the prevaporiser tubes and from the wall cooling is sufficient for the air feeding of the primary zone.

The Influence of Dilution Hole Geometry on Jet Mixing

Measurements have been made on a fully annular test facility, downstream of a row of heated dilution jets injected normally into a confined cross-flow at a momentum flux ratio of 4. The investigation concentrated on the consistency of mixing between the jets, as indicated by the regularity of the temperature pattern around the cross-flow annulus. When the heated air was supplied from a representative feed annulus, the exit velocity profile across each plunged hole was significantly altered and caused a distortion of the temperature distribution in the ensuing jet. The degree of distortion varies in a random manner, so that each jet has its own mixing characteristics thereby producing irregularity of the temperature pattern around the annulus. With the same approach and operating conditions some of the plunged dilution holes were modified, and tests on this modified sector indicated a significant improvement in the circumferential regularity of the temperature pattern. Further tests showed these modifications to the dilution holes had a negligible effect on the values of the discharge coefficients.