CN101435585B - Gas turbine combined type fuel evaporating and atomizing combustion apparatus - Google Patents

Abstract

The invention provides a combined fuel oil atomizing, evaporating and combusting device for a gas turbine, relates to an air inlet device of the gas turbine, a fuel oil atomizing, evaporating and blending device, and core technology of organized combustion and stable flame, and belongs to the power field of an aeronautic power propulsion system and a ground gas turbine. A nozzle 1 is arranged at a central position of an inlet of a premixing chamber 2; an evaporator 3 is fixed in an inner cavity of the premixing chamber 2; double cyclones 4 are arranged at the inside of the outlet end of the premixing chamber 2 and connected hermetically; a centrifugal nozzle 5 is arranged at a central position of the double cyclones 4; a venturi 6 is welded at a transition position of an outlet of internal and external cyclones of the double cyclones 4; a sleeve 7 is hermetically welded with the outside of an outlet of the premixing chamber 2; and the head of a combustion chamber 8 is hermetically welded with the sleeve 7. Compared with the prior fuel oil combined nozzle, the device has the advantages of improving properties of fuel oil atomizing, evaporating and blending and evenness of oil-gas space distribution, improving combustion performance, shortening flame length and reducing discharge of pollutant, and is a comparatively ideal combined fuel oil atomizing and combusting device for a high-performance gas turbine.

Description

A gas turbine combined fuel oil evaporation and atomization combustion device

technical field

The invention relates to a gas turbine combined fuel atomization, evaporation, and combustion device, a combined fuel atomization, evaporation, and combustion device used by aviation and ground gas turbines, which belongs to a gas turbine air intake device, a fuel atomization, evaporation and mixing device, The core technology of organizing combustion and stabilizing the flame belongs to the field of aerodynamic propulsion system and ground gas turbine power.

Background technique

At present, the fuel nozzles in gas turbine power plants at home and abroad mostly use liquid film air atomizing nozzles and combined air atomizing devices. With the development of high-performance engines, it is required to complete combustion in a shorter combustion zone, shorten the length of the combustion chamber, reduce weight, better organize the concentration field of fuel, higher requirements for ignition performance and lean flameout range, lower pollutant emissions. At the same time, high-temperature resistant fuel nozzles are a new topic. It is necessary to prevent nozzle fuel coking, because nozzle high-temperature coking has a great impact on the atomization quality and life of nozzles, and the development of fuel supply technology for low-pollution combustion chambers is still in the research of gas turbines. popular topics. Therefore, there is an urgent need for fuel atomization technology to greatly improve the fuel atomization evaporation performance and the uniformity of oil and gas distribution.

The existing fuel nozzle technologies mainly include:

①The direct injection nozzle has poor fuel atomization, small spray cone angle and narrow working range.

②The centrifugal nozzle has good atomization quality, reasonable oil mist distribution, good ignition performance and wide stable combustion range, but it is prone to smoke under high pressure and easy to accumulate coke under high temperature.

③Fuel and air pre-mixing and pre-evaporation in the way of evaporating tube oil supply, low NOX emission, no exhaust smoke, relatively stable combustion performance and temperature distribution, but there are dangers of automatic ignition, backfire, and flameout, and the stable combustion range is narrow , Poor reliability at high temperature.

④The liquid film air atomizing nozzle is a major breakthrough in fuel atomization technology, as shown in Figure 1. The nozzle is introduced to atomize the fuel by the airflow introduced into the nozzle (combustion chamber such as the mouth), and the oil film on the lip is atomized by the impact of high-speed airflow inside and outside. Small. On the engine with high pressure ratio and high temperature rise, the liquid film air atomizing nozzle ensures the full and uniform mixing of fuel and air flow, uniform outlet temperature field and less smoke exhaust, thus replacing the position of centrifugal nozzle in higher performance engines . The UK uses this nozzle on the RB211 engine.

⑤The combined air atomization device is another major breakthrough in fuel atomization technology, as shown in Figure 2. It adopts an integrated design of axial double swirlers and nozzles. The fuel is atomized once through the nozzles, and the oil film on the venturi is atomized again by the high-speed airflow on both sides. Internal and external swirlers, nozzles, venturi tubes, and sleeves all have an important impact on the atomization and mixing of fuel. Venturi tubes are similar to liquid film air atomizing nozzles. It has good ignition performance, complete combustion, wide and stable combustion range, good outlet temperature field and low emission divergence requirements. GE's E ³ has been successfully applied to the engine.

Among them, the ④ and ⑤ nozzles are currently advanced fuel atomization technologies, but there is no primary atomization premixing and pre-evaporation process of fuel, and the liquid film space distribution is narrow. Fuel atomization and gradual mixing with air are completed in the combustion chamber. There is liquid mist combustion and higher _NOx emissions.

The thermal test of the gasoline-fueled pulse detonation engine proves that the inner diameter of the detonation tube is 60mm, and the oil is supplied from the rear of the axial double-swirl pneumatic valve (one of the advanced aviation combined atomization devices), as shown in the figure 3. The peak pressure of the generated detonation wave is 1.78Mpa. When the centrifugal nozzle is moved to the front of the double cyclone to supply oil, as shown in Figure 4, the peak pressure of the generated detonation wave is 2.43Mpa, and the peak pressure is increased by 0.65Mpa. This shows that the front fuel supply is better than the rear fuel supply (existing aviation combined air atomization nozzle) to improve the fuel atomization evaporation and mixing characteristics, and to improve the knock combustion effect. The main reason is that the centrifugal nozzle supplies oil in front of the swirler, and the oil mist cone particles are evenly distributed in the converging channel formed between the swirl blades. The small oil droplets and oil vapor can move with the air flow, and the large oil droplets are at the turn of each blade. An oil film is formed on the inner side, and the oil film at the outlet of the blade is atomized by the high-speed airflow on both sides of the blade. In this way, the cyclone is equivalent to how many liquid-film pneumatic atomizing nozzles. Compared with ordinary liquid-film nozzles, the blade lip area is larger, the oil film is thinner, and the fuel atomization and mixing are good, and a uniform oil-gas mixture can be formed quickly. The centrifugal nozzle supplies fuel behind the double cyclone, and the atomization of the fuel mainly depends on the action of the Venturi tube, and the secondary pure air and the primary oil-air mixture are gradually mixed in the combustion chamber, and there is a certain difference in the concentration of oil and gas.

The fuel nozzle is a key component of the engine and plays an important role in determining the performance of the engine. The working pressure and temperature of the high-performance engine combustion chamber have been greatly increased, and the problems of smoke, coke and NO _X emissions have become increasingly prominent. The key to solving them depends on the successful application of advanced fuel supply technology to improve the quality and distribution of fuel atomization and evaporation. In terms of smoke reduction measures, the most effective is the improvement of the fuel supply method, replacing the pressure atomization nozzle with air atomization nozzle and evaporation tube. In terms of reducing _NOx emissions, the fuel injected by the nozzle of the conventional combustion chamber enters the main combustion area directly, with little or no pre-mixing with air, so the combustion occurs in a localized area close to the stoichiometric temperature, correspondingly forming high _NOx emissions . The common feature of all dry combustors is the effort to eliminate these localized high temperature zones, starting with the Dry Low Emissions (DLE) combustor. DLE combustion technology is mainly focused on the innovation of fuel supply schemes. Secondly, the common characteristics of foreign ultra-low NO _X combustion technologies are to supply uniform gas mixture, reasonably control the oil-gas ratio in the main combustion zone, and maintain combustion at a relatively low temperature. Therefore, in response to the requirements of high-performance engines, it is urgent to develop new fuel atomization technology.

Contents of the invention

In order to overcome the shortcomings of the prior art structure, the present invention provides a gas turbine combined fuel oil evaporation atomization combustion device. The combined fuel atomization evaporation combustion device of the present invention fully utilizes and retains the functions of the advanced combined air atomization combination device, supplies oil and installs an evaporator in front of the swirler, increases the function of fuel premixing and preevaporation, and fuel oil The atomization blending performance is good, and the gas phase oil-gas ratio is improved. The device can adapt to the requirements of the development of high-performance engines, can solve the problems of engine smoke, coke, high NO _X emissions, improve combustion performance and shorten the length of the combustion chamber.

The technical solution adopted by the present invention to solve the technical problem is: a combined fuel atomization evaporation combustion device, which increases the fuel premixing pre-evaporation process, makes full use of gas kinetic energy, and increases the spatial distribution of the oil film. The swirler is equivalent to Multiple liquid film pneumatic atomizing nozzles improve the fuel atomization and mixing characteristics, make the space distribution of oil and gas uniform, improve combustion performance, reduce smoke, coke and NO _X emissions, and can meet the needs of high-performance engine development.

A gas turbine combined fuel atomization evaporation combustion device, the gas turbine combined fuel atomization device consists of a nozzle, a premixing chamber, an evaporator, a double swirler, a centrifugal nozzle, a venturi tube, a sleeve, and a combustion chamber;

The nozzle is installed at the center of the inlet of the premixing chamber;

The premixing chamber refers to a straight pipe with the same outer diameter as the double cyclone, which is upstream of the double cyclone and is sealed with the outer end of the double cyclone;

The evaporator refers to a plurality of thin steel pipes welded side by side to form a blunt body assembly, which is installed inside the pre-mixing chamber, with nozzles at a certain distance upstream and double cyclones at a certain distance downstream;

The double cyclone is installed inside the outlet end of the premixing chamber and is closely connected with the premixing chamber,

The centrifugal spray group is installed at the center of the double cyclone;

The venturi tube is welded at the outlet of the inner and outer swirlers of the double swirler, upstream of the combustion chamber,

The inner side of the sleeve is welded with the premixing chamber, and the outer side is welded with the combustion chamber;

The combustion chamber is welded on the outside of the sleeve.

A gas turbine combined fuel atomization evaporation combustion device, further comprising:

The evaporator refers to a set of multiple circular tubes;

Said double swirler is composed of swirlers whose internal and external rotation directions are opposite, each swirler has a plurality of blades, the inlet and outlet are straight sections, and the middle is connected by an arc;

The centrifugal spray group refers to nozzles with small fuel flow or blow-off nozzles, and refers to nozzles with a certain diameter and wall thickness. The inner swirler blades of the double swirler are welded on it. The nozzle jet is used to blow off the oil film on the surface, the inlet is a central round hole, and the outlet is a plurality of divergent small round holes;

The Venturi tube refers to a circular tube with a certain wall thickness, the inlet is a shrinking channel, and the outlet is a gradually expanding channel;

The sleeve refers to an expansion cone with a certain thickness;

The combustion chamber refers to a hollow cavity with a certain diameter.

A gas turbine combined fuel atomization evaporation combustion device, including a nozzle, a premixing chamber, an evaporator, an axial swirler, a centrifugal nozzle, a venturi tube, a fixed seat, a radial swirler, a connecting plate, a sleeve, Combustion chamber composition;

The nozzles mentioned above refer to the fuel centrifugal spray group or atomization tank nozzles, which are installed at the center of the inlet of the premixing chamber;

The pre-mixing chamber refers to a straight pipe with the same outer diameter as the axial double swirler, which is upstream of the axial swirler and is sealingly connected to the outer end of the inlet of the axial swirler;

The evaporator refers to a double blunt body or a spiral body or a plurality of thin steel pipes welded side by side or a plurality of round pipes, installed inside the premixing chamber, a certain distance upstream is the nozzle, and a certain distance downstream is the axial direction. Cyclone;

The axial swirler refers to a swirler composed of axial blades, which is installed inside the outlet end of the premixing chamber and closely connected with the premixing chamber;

The centrifugal spray group refers to nozzles with small fuel flow, which are installed in the center of the axial swirler;

The Venturi tube refers to a circular tube with a certain wall thickness, which is welded at the outer diameter of the outlet of the axial swirler, and is closely connected with the premixing chamber, and is located upstream of the combustion chamber.

The fixed seat refers to a circular steel plate with a certain thickness, which is welded circumferentially with the premixing chamber at the inner diameter, and welded with the radial cyclone at the outer diameter;

The radial swirler refers to a swirler composed of radial blades, the upstream is welded to the fixed seat, and the downstream is welded to the connecting plate;

The connecting plate refers to a circular steel plate with a certain thickness, which is welded upstream to the radial swirler, downstream to the inner side to the sleeve, and the outer side to the wall of the combustion chamber.

The sleeve refers to an expansion cone with a certain thickness, which is welded to the inner side of the connecting plate;

The combustion chamber refers to a hollow cavity with a certain diameter, which is welded to the outside of the connecting plate;

The beneficial effect of the present invention is to make full use of the function of the advanced combined air atomization combination device, adopt the fuel supply in front of the double swirler, set the evaporator downstream of the fuel nozzle, and use the swirl vane to atomize the premixed fuel, which has the following advantages :

①. The fuel primary atomization premixing pre-evaporation process is added, which greatly improves the fuel atomization evaporation and mixing performance, and increases the gas phase oil-gas ratio.

②. The cyclone is equivalent to multiple liquid-film pneumatic atomizing nozzles, which realizes fuel oil graded atomization and blending, and greatly improves the quality of fuel atomization and blending and the uniformity of oil and gas space distribution.

③. Expand the function of the venturi tube to atomize fuel, the oil mist can form an oil film on the inner and outer surfaces of the venturi tube, and get good fuel atomization quality.

④. Utilize the switching of the front and rear nozzles of the swirler to expand the stable combustion range and realize "soft ignition".

⑤. Improve combustion performance, shorten flame length, avoid high temperature coking, and achieve low pollution emissions.

Therefore, a combined fuel atomization evaporation combustion device of the present invention has the advantages of improving the fuel atomization evaporation mixing performance and the uniformity of oil and gas space distribution, improving combustion performance, and realizing efficient and clean combustion. It is an ideal high-performance engine. A new generation of combined fuel atomization device.

Description of drawings

The schematic diagram of the liquid film air atomizing nozzle of Fig. 1 prior art;

The biaxial combined air atomization device of Fig. 2 prior art;

Fig. 3 is a schematic diagram of a combined nozzle (pneumatic valve) in which the nozzle in the prior art supplies oil behind the double swirler.

Fig. 4 is a schematic diagram of a combined nozzle (pneumatic valve) in which the nozzle of the prior art supplies oil in front of the double swirler.

Fig. 5 is a structural schematic diagram of the first scheme of the gas turbine combined fuel atomization evaporation combustion device;

Fig. 6 is a schematic diagram of the second structure of the combined fuel atomization, evaporation and combustion device;

The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

Detailed ways

Example 1:

A combined fuel atomization device for a gas turbine, comprising a nozzle 1, a premixing chamber 2, an evaporator 3, a double swirler 4, a centrifugal nozzle 5, a venturi tube 6, a sleeve 7 and a combustion chamber 8.

The nozzle 1 refers to the fuel centrifugal spray group or other nozzles (such as atomizing tank nozzles), which are installed at the center of the inlet of the premix chamber 2; A straight pipe with the same diameter, it is in the upstream of the double cyclone 4, and is sealed with the outer end of the double cyclone 4; the evaporator 3 refers to a plurality of thin steel pipes welded in parallel (or a plurality of round pipes set or blunt body, etc.), installed inside the premixing chamber 2, a certain distance upstream is the nozzle, and a certain distance downstream is the double cyclone 4; Composed of cyclones, each cyclone has multiple blades, the inlet and outlet are straight sections, and the middle is connected by an arc. It is installed inside the outlet end of the premixing chamber 2 and is closely connected with the premixing chamber 2. Centrifugal spray group 5 refers to nozzles with small fuel flow (or blowing nozzles, which refer to nozzles with a certain diameter and wall thickness, on which the inner swirler blades of the double swirler 4 are welded, and the multiple circular nozzles of the nozzle The orifice jet is used to blow off the oil film on the surface, the inlet is a central circular hole, and the outlet is a plurality of divergent small circular holes), which is installed in the center of the double swirler 4; the venturi 6 refers to a A round pipe with a certain wall thickness, the inlet is a reduced channel, and the outlet is a gradually expanding channel. It is welded at the outlet of the inner and outer swirlers of the double swirler 4 and is located upstream of the combustion chamber 8. The sleeve 7 is Refers to the expansion cone with a certain thickness, its inner side is welded with the premixing chamber 2, and the outer side is welded with the combustion chamber 8;

Installation sequence: the evaporator 3 is fixed in the inner cavity of the premixing chamber 2; the nozzle 1 is fixed at the center of the inlet of the premixing chamber 2; the venturi tube 6 is welded at the transition position of the inner and outer swirlers of the double swirler 4; the centrifugal nozzle 5 is installed at the center of the double swirler 4; the double swirler 4 is installed on the inner side of the outlet end of the premixing chamber 2 and tightly connected; the sleeve 7 is sealed and welded to the outside of the outlet of the premixing chamber 2; the head of the combustion chamber 8 is connected to the sleeve Barrel 7 is sealed and welded.

Example 2:

A gas turbine combined fuel atomization evaporation combustion device, including a nozzle 1, a premixing chamber 2, an evaporator 3, an axial swirler 12, a centrifugal nozzle 5, a venturi tube 6, a fixed seat 7, and a radial swirler 8. It is composed of connecting plate 9, sleeve 10 and combustion chamber 11.

The nozzle 1 refers to the fuel centrifugal spray group or other nozzles (such as atomization tank nozzles), which are installed at the center of the inlet of the premix chamber 2; the premix chamber 2 refers to the 4 straight pipes with the same outer diameter, which are in the upstream of the axial swirler 12 and sealed with the inlet outer end of the axial swirler 12; the evaporator 3 refers to double blunt bodies (or spiral bodies or multiple Thin steel pipes are welded side by side or a plurality of round pipes are set), installed inside the premixing chamber 2, a certain distance upstream is the nozzle, and a certain distance downstream is the axial swirler 12; the axial swirler 12 refers to a swirler composed of axial blades, which is installed inside the outlet end of the premix chamber 2 and is closely connected with the premix chamber 2; the centrifugal spray group 5 refers to a nozzle with a small fuel flow rate, which At the central position of the axial swirler 12; the venturi tube 6 refers to a circular tube with a certain wall thickness, which is welded at the outlet outer diameter of the axial swirler 12 and is tightly connected to the premixing chamber 2 Connected, located upstream of the combustion chamber 8, the fixed seat 7 refers to a circular steel plate with a certain thickness, which is welded circumferentially with the premixing chamber 2 at the inner diameter, and welded with the radial swirler 8 at the outer diameter; The radial swirler 8 refers to a swirler composed of radial blades, which is welded with the fixed seat 7 upstream and welded with the combustion chamber 11 downstream: the connecting plate 9 refers to a circular ring with a certain thickness Steel plate, its upstream is welded with the radial swirler 8, the inner side of the downstream is welded with the sleeve 10, and the outer side is welded with the wall of the combustion chamber 11: the sleeve 10 refers to an expansion cone with a certain thickness, and it is connected with the connecting plate 9 internal welding; the combustion chamber 11 refers to a hollow cavity with a certain diameter, which is welded with the connecting plate 9 outside.

Installation sequence: the evaporator 3 is fixed in the inner cavity of the premixing chamber 2; the nozzle 1 is fixed in the center of the inlet of the premixing chamber 2; the venturi tube 6 is welded at the outer diameter of the outlet of the axial swirler 12; the centrifugal nozzle 5 is installed At the center of the axial swirl 12; the axial swirl 12 is installed on the inner side of the outlet of the premixing chamber 2 and is tightly connected; the fixed seat 7 is welded to the radial swirl 8, and the connecting plate 7 is connected to the radial swirl The device 8 is welded; the sleeve 10 is sealed and welded with the connecting plate 9; the combustion chamber 11 is sealed and welded with the connecting plate 9; the fixing seat 7 is sealed and welded with the premixing chamber 2.

Embodiment 3: As shown in Fig. 5, it is a structural schematic diagram of the first scheme of the gas turbine combined fuel atomization evaporation combustion device. It consists of a nozzle 1, a premix chamber 2, an evaporator 3, a double swirler 4, a centrifugal nozzle 5, a venturi tube 6, a sleeve 7 and a combustion chamber 8. The nozzle 1 is installed at the center of the inlet of the pre-mixing chamber 2; Sealed connection; the evaporator 3 is installed inside the premixing chamber 2, the nozzle is a certain distance upstream, and the double cyclone 4 is a certain distance downstream; the double cyclone 4 is installed inside the outlet end of the premixing chamber 2, and is connected with the premixing The chamber 2 is tightly connected, and the centrifugal nozzle 5 is installed at the center of the double swirler 4; the venturi tube 6 is welded at the outlet of the inner and outer swirlers of the double swirler 4, upstream of the combustion chamber 8; the inner side of the sleeve 7 It is welded with the premix chamber 2, and the outer side is welded with the combustion chamber 8; the combustion chamber 8 is welded with the outer side of the sleeve 7.

Solution 1 of the present invention adopts the nozzle 1 to be installed upstream of the evaporator 3, and through the adjustment of the relative position, it is ensured that the nozzle 1 travels upstream of the evaporator 3 to form a uniform oil mist field, and the oil mist is on the surfaces of the evaporator 3 (including the premixing chamber) surface) to form an oil film, which moves downstream under the action of the airflow, and is atomized by the high-speed airflow at the outlet of the evaporator 3, so that the oil and gas are mixed evenly; the premixing chamber 2 should not only reduce the air intake resistance, but also ensure sufficient air intake channels area, control a reasonable air velocity, and prevent tempering while ensuring good atomization. It is sealed with the cyclone; As long as it is assembled in one piece or a combination of blunt bodies), the outer edge can be in contact with the inner wall of the premixing chamber 2. The diameter and quantity of the straight pipe should be determined according to the blockage ratio and air velocity. A large amount of oil mist forms an oil film on its surface and atomizes and evaporation; the double swirler 4 is installed at the outlet of the premixing chamber 2 and downstream of the evaporator 3, and the oil mist forms an oil film on the swirl blade again, and the oil film is atomized and mixed by the airflow on both sides of the blade, so that it enters the combustion chamber 8 The head is a uniform mixture of oil and gas, and the gas phase oil-gas ratio is improved; the centrifugal nozzle 5 is installed at the center of the double swirler 4, and only the centrifugal nozzle 5 supplies oil when the combustion starts and the load is small, which can ensure good ignition performance and Wide and wide lean oil stable combustion boundary reduces the emission of pollutants; the venturi tube 6 is installed at the outlet of the inner and outer swirlers of the double swirler 4, so that the oil mist of the centrifugal nozzle 5 forms an oil film on it, or only When the nozzle 1 supplies oil, the oil mist atomized by the blade forms an oil film on it, and the oil film is atomized by the high-speed airflow on both sides, and at the same time changes the function of the recirculation zone; the inner side of the sleeve 7 is welded to the premixing chamber 2, and the outer side is connected to the combustion chamber 8 is welded to change the structure of the flow field and has an evaporation effect on the oil film on it; the head of the combustion chamber 8 is sealed and welded to the sleeve 7, which is the combustion space for the oil-gas mixture.

Solution 1 of the present invention The working process of the combined fuel atomization, evaporation and combustion device is as follows: first, the combustion chamber is supplied with air, and only the centrifugal nozzle 5 is supplied with fuel during startup and light load, and the atomized fuel forms an oil film on the inner surface of the Venturi tube , being atomized by the high-speed airflow on both sides, an oil-gas mixture with a certain atomization quality and spatial distribution is formed in the combustion chamber 8, the ignition is successful, and the boundary of lean flameout is improved. At high power and full load, the centrifugal nozzle 5 is closed, and only nozzle 1 supplies oil. The fuel is sprayed and atomized from nozzle 1, and mixed with air flow to form a certain oil mist field. The oil mist is mixed in the evaporator 3 and premixed The oil film is formed on the surface of the chamber 2 and evaporated. Under the action of the air flow, the oil film moves to the outlet of the evaporator 3 and is atomized again by the high-speed air flow. The small oil droplets have small inertia and flow out of the cyclone 4 with the airflow, and the larger oil droplets form an oil film again on the inner surface of the blades of the cyclone 4, and are atomized by the high-speed airflow on both sides at the blade outlet. A small amount of oil droplets will form an oil film on the inner surface of the venturi tube 6 and be atomized by the high-speed airflow on both sides, and all the oil mist and oil vapor will enter the combustion zone with the airflow. There are as many atomizing lips as there are blades in the swirler 4, which is equivalent to how many liquid-film pneumatic atomizing nozzles. The fuel atomized particles are fine and the space is evenly distributed. At the same time, the high-temperature blades have an evaporation effect on the oil film. . A small part of the oil droplets forms an oil film on the sleeve 7 and evaporates, and is atomized by the airflow of the combustion chamber 8, thereby forming a high gas-phase oil-gas ratio, a well-atomized oil mist and a reasonable spatial distribution. When the combustion chamber is working, the temperature of all components rises, which greatly improves the evaporation of fuel, so that the combustion chamber has good combustion performance, low fuel-air ratio operation can achieve low NOX emissions, and avoid nozzle 1 coking and clogging.

Example 4:

Fig. 6 is a structural schematic diagram of the second scheme of the gas turbine combined fuel atomization evaporation combustion device. It is connected by nozzle 1, premixing chamber 2, evaporator 3, axial swirler 12, centrifugal nozzle 5, venturi tube 6, sleeve 7, combustion chamber 8, fixed seat 9, radial swirler 10, Plate 11 is composed.

The nozzle 1 is installed at the center of the inlet of the pre-mixing chamber 2; The outer end of the evaporator is sealed and connected; the evaporator 3 is installed inside the premixing chamber 2, the nozzle is a certain distance upstream, and the axial swirler 12 is a certain distance downstream; the axial swirler 12 is installed inside the outlet end of the premixing chamber 2 , and tightly connected with the premixing chamber 2, the centrifugal nozzle 5 is installed at the center of the axial swirler 12; position; the venturi tube 6 is welded at the outlet of the axial swirler 12, and is closely connected with the premix chamber 2, and is upstream of the combustion chamber 11; the fixed seat 9 is welded with the premix chamber 2 circumferentially near the inner diameter, and The outer diameter is welded with the radial swirler 8; the upstream of the radial swirler 10 is welded with the fixed seat 9, and the downstream is welded with the combustion chamber 11: the upstream of the combustion chamber 8 is welded with the radial swirler 10, and the inner side of the downstream is welded with the sleeve The cylinder 10 is welded, and the outer side is welded with the tube wall of the radial swirler 10: the fixed seat 9 is welded with the inner side of the connecting plate 11; the radial swirler 10 is welded with the outer side of the combustion chamber 8.

The second scheme of the present invention adopts the nozzle 1 to be installed on the upstream of the evaporator 3, and through the adjustment of the relative position, it is ensured that the nozzle 1 forms a uniform oil mist field on the upstream of the evaporator 3, and the oil mist is on the surfaces of the evaporator 3 (including the premixing chamber) surface) to form an oil film, which moves downstream under the action of the airflow, and is atomized by the high-speed airflow at the outlet of the evaporator 3, so that the oil and gas are mixed evenly; the premixing chamber 2 should not only reduce the air intake resistance, but also ensure sufficient air intake channels area, control a reasonable air velocity, and prevent backfire while ensuring good atomization. It is sealed with the cyclone; According to the required air velocity, determine the clogging ratio of the blunt body, a large amount of oil mist forms an oil film on its surface and atomizes and evaporates; the axial swirler 12 is installed on the inside of the outlet of the premixing chamber 2 and on the side of the evaporator 3 Downstream, the oil mist forms an oil film again on the swirl blade, and the oil film is atomized and mixed by the high-speed airflow on both sides of the blade, so that the outlet of the axial swirler 12 is a uniform mixture of oil and gas; the centrifugal nozzle 5 is installed on the axial swirler 12 in the center position; when the combustion is started and the load is small, only the centrifugal nozzle 5 supplies oil, which can ensure good ignition performance and a wide fuel-lean stable combustion boundary, reducing the emission of pollutants; the venturi tube 6 is installed on the shaft At the outlet of the cyclone 12, let the oil mist of the centrifugal nozzle 5 form an oil film on it, or when only the nozzle 1 supplies oil, the oil mist part atomized by the blade forms an oil film on it, and the oil film is atomized by the high-speed airflow on both sides At the same time, the effect of the reflow zone is changed; the fixed seat 9 is welded to the premixing chamber 2; the radial swirler 10 is welded to the fixed seat 9 to ensure the air flow space at the outlet of the radial swirler 10, forming the external swirling air flow of the venturi tube 6, The rotation direction of the airflow is opposite to the rotation direction of the airflow of the axial swirler 12 to ensure the atomization quality of the fuel at the outlet of the venturi tube 6; the connecting plate 11 is welded to the radial swirler 10; the sleeve 10 is connected to the inner side of the connecting plate 11 Welding changes the flow field structure and evaporates the oil film on it; the combustion chamber 10 is welded to the outside of the connecting plate 11, which is the combustion space for the oil-gas mixture.

The working process of the combined fuel atomization, evaporation and combustion device of the second scheme of the present invention is as follows: firstly, the combustion chamber is supplied with air, and only the centrifugal nozzle 5 is supplied with fuel during startup and light load, and the atomized fuel forms an oil film on the inner surface of the Venturi tube , being atomized by the high-speed airflow on both sides, an oil-gas mixture with a certain atomization quality and spatial distribution is formed in the combustion chamber 8, the ignition is successful, and the boundary of lean flameout is improved. At high power and full load, the centrifugal nozzle 5 is closed, and only nozzle 1 supplies fuel, and the fuel is sprayed and atomized from nozzle 1, and mixed with the airflow in the premixing chamber 2 to form a certain oil mist field, and the oil mist evaporates An oil film is formed on the surface of the evaporator 3 and the premixing chamber 2 and evaporates. Under the action of the air flow, the oil film moves to the outlet of the evaporator 3 and is atomized again by the high-speed air flow. The small oil droplets have low inertia and flow out of the axial swirler 12 with the airflow, and the larger oil droplets form an oil film on the inner surface of the blades of the axial swirler 12, and are atomized by the high-speed airflow on both sides at the blade outlet. A small amount of oil droplets will form an oil film on the inner surface of the venturi tube 6 and be atomized by the high-speed airflow on both sides, and all the oil mist will enter the combustion zone with the airflow. The axial swirler 12 is equivalent to a plurality of liquid-film pneumatic atomizing nozzles. The fuel atomized particles are fine and evenly distributed in space. At the same time, the high-temperature blades have an evaporation effect on the oil film. The radial swirler 10 provides the venturi tube 6 with an external swirling air flow, changes the structure of the flow field, and prevents coking and carbon deposits on the wall of the flame tube. A small part of the oil droplets forms an oil film on the sleeve 10 to evaporate and is atomized by the airflow of the radial swirler 10 . Thus forming a high gas phase oil-gas ratio, well-atomized oil mist and reasonable spatial distribution. When the combustion chamber is working, the temperature of all components rises, which greatly improves the evaporation of fuel, so that the combustion chamber has good combustion performance, low fuel-air ratio operation can achieve low _NOx emissions, and avoid nozzle 1 coking and clogging.

As can be seen from the above description, the present invention increases the function of fuel premixing and pre-evaporation by supplying oil and setting an evaporator in front of the swirler. The fuel oil forms an oil film and atomizes and evaporates for many times, which gradually improves the gas phase oil-gas ratio and the mixing effect of fuel atomization and evaporation, so that the oil-gas space is evenly distributed. The matching of the centrifugal nozzle 5 and the nozzle 1 expands the stable combustion working range. The invention can meet the needs of high-performance engines and dry combustion chambers through rational design.

The gas turbine combined fuel atomization evaporation combustion device of the present invention. The scope of application is that the fuel flow rate is 10-100g/s, the minimum throat airflow velocity is greater than 50m/s, and the inlet airflow temperature is less than 700 degrees Celsius. It improves the quality of fuel atomization, evaporation and mixing, improves combustion performance, and can achieve low _NOx combustion. The invention can be used as an ideal combined fuel atomizing device for a high-performance gas turbine or a dry combustion chamber.

Claims (10)

1. gas turbine combined type fuel-oil atmozation combustion by evaporation device, it is characterized in that this gas turbine combined type fuel atomization device comprises that fuel nozzle, premixer, evaporimeter, twin shaft are to cyclone, swirl atomizer, Venturi tube, sleeve, combustion chamber composition;

Described fuel nozzle is installed in the import center of premixer;

Described premixer be meant with twin shaft to the identical straight tube of cyclone external diameter, it is tightly connected with the outer end of twin shaft to cyclone in the upstream of twin shaft to cyclone;

Described evaporimeter refers to the bluff body assembly that a plurality of fine steel tubes are welded side by side, is installed in inside, premixer, and its upstream certain distance is a fuel nozzle, and the downstream certain distance is that twin shaft is to cyclone;

Described twin shaft is installed in the inside of premixer's port of export to cyclone, and closely is connected with the premixer,

Described swirl atomizer is installed in the center of twin shaft to cyclone;

Described Venturi tube is welded on the exit of twin shaft cyclone inside and outside cyclone, is in the upstream of combustion chamber,

Described sleeve is inboard to be welded with the premixer, the outside and combustion chamber welding;

Described combustion chamber is welded on the outside of sleeve.

2. a kind of combination gas oil atomization combustion by evaporation device according to claim 1 is characterized in that,

Described evaporimeter is to be formed by a plurality of pipe suits;

Described twin shaft is made up of the opposite cyclone of inside and outside direction of rotation to cyclone, and each cyclone has a plurality of blades, imports and exports to be straight section, and the centre connects with circular arc.

3. a kind of combination gas oil atomization combustion by evaporation device according to claim 1 is characterized in that,

Described swirl atomizer is meant the nozzle of little fuel flow or is the blowing nozzle, be meant nozzle with certain diameter and wall thickness, twin shaft welds on it to the interior swirler blades of cyclone, the a plurality of circular spray orifice jet of shower nozzle is in order to blow down the oil film on surface, import is a center hole, exports the small sircle hole of dispersing for a plurality of.

4. a kind of combination gas oil atomization combustion by evaporation device according to claim 1 is characterized in that,

Described Venturi tube is meant the pipe with certain wall thickness, and import is for reducing the shape passage, exports to be the gradually expanded form passage.

5. a kind of combination gas oil atomization combustion by evaporation device according to claim 1 is characterized in that,

Described sleeve is meant to have certain thickness diverging cone;

Described combustion chamber is meant the hollow cavity with certain diameter.

6. according to claim 1,2,3,4 or 5 described a kind of combination gas oil atomization combustion by evaporation devices, it is characterized in that, described fuel nozzle at twin shaft to cyclone the place ahead fuel feeding.

7. according to claim 1,2,3,4 or 5 described a kind of gas turbine combined type fuel-oil atmozation combustion by evaporation devices, it is characterized in that described fuel nozzle is at evaporimeter the place ahead fuel feeding, evaporimeter is arranged on twin shaft to cyclone the place ahead.

8. a gas turbine combined type fuel-oil atmozation combustion by evaporation device is characterized in that, comprises fuel nozzle, premixer, evaporimeter, axial swirler, swirl atomizer, Venturi tube, holder, radial swirler, connecting plate, sleeve, combustion chamber composition;

Described fuel nozzle is installed in the import center of premixer;

Described premixer is meant and the axial identical straight tube of double cyclones external diameter, in the upstream of axial swirler, is tightly connected with the import outer end of axial swirler;

Described evaporimeter is meant two bluff body or conveyor screws or a plurality of fine steel tube is welded side by side or a plurality of pipe suit forms, and is installed in inside, premixer, and its upstream certain distance is a nozzle, and the downstream certain distance is an axial swirler;

Described axial swirler is meant the cyclone of being made up of axial blade, is installed in the inside of premixer's port of export, and closely is connected with the premixer;

The centrifugal spray group of stating is meant the nozzle of little fuel flow, is installed in the center of axial swirler;

Described Venturi tube is meant the pipe with certain wall thickness, is welded on the outlet outer radius of axial swirler, and closely is connected with the premixer, is in the upstream of combustion chamber,

Described sleeve is meant to have certain thickness diverging cone, with the inboard welding of connecting plate;

Described combustion chamber is meant the hollow cavity with certain diameter, with the welding of the connecting plate outside;

Described holder is meant to have certain thickness ring steel plate, circumferentially welds by inner radius and premixer, by outer radius and radial swirler welding;

Described radial swirler is meant the cyclone of being made up of radial blade, upstream and holder welding, downstream and connecting plate welding;

Described connecting plate is meant to have certain thickness ring steel plate, upstream and radial swirler welding, and the downstream gets inboard and the sleeve welding, the outside and the welding of combustion chamber tube wall.

9. a kind of combination gas oil atomization combustion by evaporation device according to claim 8 is characterized in that described fuel nozzle is at cyclone the place ahead fuel feeding.

10. a kind of gas turbine combined type fuel-oil atmozation combustion by evaporation device according to claim 8 is characterized in that described fuel nozzle is at evaporimeter the place ahead fuel feeding, and evaporimeter is arranged on axial swirler the place ahead.

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