Effective date : Year of fee payment : 4. Year of fee payment : 8. Disclosed is a triple swirl gas turbine combustor using various fuels such as coal gas, DiMethyl Ether, and waste gas generated in an ironworks in a gas turbine. The triple swirl gas turbine combustor combusts three different fuels simultaneously or individually and various fuels such as LCV gas and HCV gas so that fuel flexibility can be improved. Swirl generated in a second swirler of the triple swirler is reversely jetted to increase a mixing degree of a fuel-air mixture and an intensity of a turbulent flow so that combustion efficiency can be increased, harmful exhaust gas can be reduced and vibration can be reduced. The present invention relates to a triple swirl gas turbine combustor and, more particularly to, a triple swirl gas turbine combustor in which a combustion performance, overall available rate, and fuel flexibility of a gas turbine are increased. In recent years, since energy price is increased and global warming becomes more serious, it significantly needs to increase efficiency of a power generating facility and to develop technology using new renewable energy. An integrated gasification combined cycle IGCC using a gas turbine is a current power generating system having the highest efficiency. Since the IGCC can gasify biomass, coal, and garbage such as waste carpet to generate electricity when a gasification system is coupled therewith, the IGCC is useful to generate electric power using various types of fuels.
Triaxial Swirler Liquid Injector Development
The present invention relates generally to gas-turbine unit, relates more specifically to combustion chamber wherein. In gas-turbine unit, compressor compresses air, and burns with fuel mix in the combustion chamber and produce the heat combustion flow that flows to downstream and the turbine by extraction energy at different levels.
High-pressure turbine drives compressor, and low-pressure turbine is then for example done useful work in a typical aviation with the upstream fan in the turbofan formula gas-turbine unit by driving. The performance of combustion chamber is crucial for the overall performance of gas-turbine unit. In typical toroidal combustion chamber, use one to arrange the independently vaporizer and the fuel nozzle that matches of cyclone form.
Before burning fuel oil is mixed with air, combustion chamber diffluence is downstream passed through in the combustion gas of generation, and is discharged into turbine.
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What Does Swirl Mean In African American Culture?
Kind code of ref document : A1. Ref country code : DE. Ref legal event code : Effective date : A premix burner for a gas turbine for use in power generation plants, comprises an axial swirler 12 to which pilot fuel gas and pilot air flow are delivered, and a duct for the premix flow 9 extending annularly and diagonally around said axial swirler 12 , which contains a diagonal swirler 8 to which premix fuel gas and premix air are delivered.
The swirler swirls the incoming air to thoroughly blend it with the fuel supplied by the fuel Publication number Priority date Publication date Assignee Title.
The computer code used for this purpose is first validated with the available experimental data. The effects of change in the percentage flow rate through the swirler, the swirl number, the hub diameter of the swirler and the diameter of the primary injection holes which influences the velocity of the jets are estimated first. It is found that the flow rate through the swirler and the size of the primary injection hole have much more influence on the characteristics of the recirculation zone than the swirl number and the hub diameter of the swirler.
But the earlier studies show that for a given flow rate through the swirler, the swirl number and swirler geometry have considerable influence on the characteristics of the recirculation zone in the absence of primary jets. Therefore it is inferred that there may be a critical point, based on the ratio of flow rate through the swirler to that of primary holes, beyond which the effects of swirl number and the swirler geometry dominate the effect of primary jets in determining the characteristics of the recirculation zone.
This critical point is determined by gradually reducing the flow through the primary holes. It is found that, initially, the recirculation ratio ratio of the mass of fluid recirculated to that sum of the mass flow rate through the swirler and through that of primary hole reduces because of weakening of the primary jets but after the critical point it increases because of the swirler effect taking over the role of providing the recirculation.
EP1710503B1 – Fuel injector bearing plate assembly and swirler assembly – Google Patents
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Heat transfer enhancement in circular tubes using helical swirl generator insert at the A.W. Date, J.R. SinghamNumerical prediction of friction factor and heat.
This invention relates to an air cooling system in gas turbine engines and more particularly to a swirl nozzle means in the air cooling system to direct cooling air from a turbine nozzle vane tangentially against a turbine wheel. Hot gas turbine engines employ one or more combustion chambers in which the combustion of a fuel air mixture generates a supply of hot gas. The hot gas is directed from the combustion chamber to one or more turbine wheels where the hot gas is caused to flow between turbine buckets or blades which are mounted in a peripheral row on each turbine wheel.
These buckets or blades react to the impinging hot gas to convert energy in the gas to rotational movement of the turbine wheels. In some cases, the turbine wheels are mounted on a common shaft with an air compressor and the rotating turbine wheels then also drive the compressor which supplies air for fuel combustion in the engines. Because the engine utilizes a large supply of very hot gases flowing therethrough, a number of components and engine structures which are exposed to the hot gas are caused to reach very high temperatures.
In some cases, the temperatures of these parts and components reach a level where they are potentially structurally detrimental. In such cases, cooling air may be taken from the compressor and utilized to cool the noted components and structures. Such cooling air may have a substantial velocity component so that due care must be exercised with regard to the direction of the cooling air in impinging on parts of the engine which may be moving or rotating at very high RPM.
Further, a significant volume of coolant air is utilized, and its ultimate disposal within the engine in an advantageous manner is desirable. It is an object of this invention to conduct a supply of coolant air, flowing through the nozzle guide vanes of a hot gas turbine engine, along an appropriate flow path, to be discharged as a jet air stream tangentially adjacent a preceding one of a pair of turbine wheels in the direction of rotation of the preceding wheel.
It is another object of this invention to provide an improved swirl nozzle in the jet air stream to impose a turning effect on the jet air stream and cause it to be directed in a tangential direction adjacent a turbine wheel in the direction of rotation thereof. It is another object of this invention to provide for ultimate disposal of the described jet air stream into the mass flow of air through the engine.
The coolant air flowing through the nozzle vanes between a pair of turbine wheels in a hot gas turbine engine is directed through appropriate conduits to an aperture in a wall facing a turbine wheel.
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A swirl port extends from the sidewall of the flow channel though the flow directing body to Rolls-Royce PLC; Original Assignee: Rolls-Royce PLC; Priority date.
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Effective date : A swirler for mixing fuel and air is provided. The swirler includes a plurality of vanes positioned radially around a central axis of the swirler and a plurality of mixing channels for mixing fuel and air. At least one mixing channel of the plurality of mixing channels is defined by opposite walls of two adjacent vanes of the plurality of vanes. The at least one mixing channel includes at least one fuel injection opening arranged at an upstream sections of the at least one mixing channel.
The at least one mixing channel also includes an axial swirler arranged at a downstream section of the at least one mixing channel.