Fuel injector with improved durability and stabilizing the flame and allow the node injector (options)

 

Fuel injector 10 to the combustion chamber of a gas turbine includes at least two arcuate cylindrical section 18, forming a radially outer boundary of the mixing chamber 28. Each adjacent pair of cylindrical sections also forms the inlet window 36 to inlet stream of primary combustion air tangentially into the mixing chamber. Sections also contain distributed in the axial direction of the multiple channels 42 supply the primary fuel injection of the primary fuel into the flow of primary air. The Central boss 46 of the fuel injector contains a cooled drum jets and evaporation nozzle 50 for supplying secondary fuel and secondary air into the combustion chamber. The nozzle 50 includes a breaker plate 74 with many cutting channels 76 and end cap 104 with multiple exhaust channels. Air channels and outlet channels do not coincide with each other, so that the secondary air discharged from the pneumatic channels, slams into the end cap and flows through the middle exhaust ports for cooling the nozzle through the blow jets of air and evaporation. The invention increases the efficiency of the cooling nozzle and the resource of its work. 3 S. and 9 C.p. f-crystals, 7 Il.

During the combustion of fossil fuels produces a number of undesirable substances, including nitrogen oxides (NOx) and carbon monoxide (CO). The destruction in the environment of substances such as NOxand, is the subject of increasing concern, and it enhances the interest in suppressing the formation of NOxand WITH devices that burn fuel.

One of the main strategies to slow the formation of NOxis the burning air-fuel mixture, which is running at the stoichiometric depleted and thoroughly mixed. Lean stoichiometry and thorough mixing make the flame temperature of combustion uniformly low, which is a prerequisite to slow the formation of NOx. One type of fuel injector, prigotovleniya depleted, thoroughly mixed mixture of fuel and air, is a nozzle with a tangential inlet. Examples of nozzles with a tangential inlet for gas turbines is described in U.S. patent 5307643, 5402633, 5461865 and 5479773 belonging to the applicant neston from the axis of the cylindrical sections, the respective segments of the cylinder.

Adjacent edges of the cylindrical sections to form an air inlet window (gap) air inlet tangentially into the mixing chamber. Multiple channels for injection of fuel are located in the axial direction along the length of each slit. The Central component (box) fuel injector passes from the front end of the nozzle towards the tail end (the output end) and forms a radially inner boundary of the mixing chamber. The insert may contain a means of providing additional fuel into the mixing chamber. During engine operation, the flow of air for combustion flows into the mixing chamber tangentially through the air inlet slits, while the fuel is injected into a stream of air through each of the channels of the fuel. The fuel and air to form a vortex around the insert and carefully and evenly mixed with each other in the mixing chamber. The fuel-air mixture flows in the axial direction toward the output end and is fed into the combustion chamber of the engine where the mixture is ignited and burns. Thorough and uniform premixing of fuel and air in the mixing chamber slows the formation of NOxblagodarya, inherent in the above described nozzles with tangential entry, they are also not free from certain drawbacks. One of the drawbacks is that the presence of an air-fuel mixture in the mixing chamber may facilitate migration of the flame into the mixing chamber where the flame quickly destroys the cylindrical section and the Central box. The second drawback relates to the tendency of spatial and temporal instability of the flame, even if it remains outside the mixing chamber. This instability of the flame, which is formally known as aeroturbine acoustic resonance manifests itself in the position fluctuations of the flame and is accompanied by low-frequency pressure fluctuations. The repetitive nature of the pressure fluctuations can have an impact on the combustion chamber, to jeopardize its structural integrity and reduce its service life. The enhanced design of the fuel injector with a tangential inlet, aimed at eliminating these disadvantages, as described in application for U.S. patent 08/991032 of 15 December 1997, the rights to which are owned by the applicant of the present application. Described nozzle contains a special set toplivopodajushchih channels for fuel injection in Asim prohealthcare end part, combined with an exit plane of the nozzle. Outlet of the fuel and air pass through the end part of the Central insert for supplying streams of fuel and air into the combustion chamber in the plane of the release nozzle. The set of channels and the shape of the Central insert is designed in such a way as to prevent the absorption of the flame and to provide back moving flame front. Loooveeeee the end part, which is the fuel that creates a surface for fixing the flame front combustion, improving the stability of the flame, and additionally counteracts any desire flames to move in the mixing chamber. The air flowing through the outlet openings in the end portion, helps to maintain combustion and cool the end part.

Although the improved nozzle is aimed at solving the stability of the flame and eliminate suction flame, the life of the nozzle may be insufficient for long trouble-free operation. Since the end of the insert is right under the influence of the flame front combustion, it works at high enough temperatures, limiting its lifetime. The speed and amount of coolant without the. what, however, increase the amount of cooling air and speed leads to destabilization of the flame of combustion due to the weakening of its properties to stay at the end.

Increasing the amount of cooling air is undesirable, as the cooling air not only cools the end part, but also reduces the flame temperature. Although at a low temperature flame is suppressed by the formation of NOxthe low flame temperature also slows down the combustion reaction that converts carbon monoxide in a more "friendly" to the environment carbon dioxide. Thus, despite the fact that the content of NOxmay be satisfactory, the content may be unacceptably high.

Thus, what is needed is an improved fuel injector with premixing, which has a balance of conflicting requirements, high durability and very high stability of the flame without increasing the CO content in the combustion products.

Thus, the present invention is the creation of a fuel injector and pre-mix, in which a suppression of the formation of NOxand WITH that comes stabilitatem fuel injector with premixing contains a Central component (box) for stabilization of a flame from the exhaust nozzle, cooled by a blow of air jets and evaporation. Very high efficiency shock and evaporative cooling improves thermal resistance of the nozzle, making it suitable for long trouble-free operation. Since the design has a high cooling efficiency, the value of the velocity of the cooling air is quite reasonable to ensure the stability of the combustion flame. Accordingly, the required amount of cooling air is quite moderate, so that emissions of CO remains at an acceptable low level.

More specifically fuel injector for a combustor of a gas turbine installation according to the invention contains:

at least two arcuate cylindrical sections, each of which has an axis located essentially parallel to the Central axis of the nozzle and radially displaced from it, and the cylindrical section to form a radially outer boundary of the mixing chamber, each adjacent pair of cylindrical sections also forms the inlet box, inlet flow of primary air into the mixing chamber and at least one of the cylindrical sections contains distributed in the axial direction of the channels of the fuel the PLO, shell located in the axial direction from the base to the nozzle, and a Central insert forms a radially inner boundary of the mixing chamber and the radially outer boundary of the duct of the secondary air and said nozzle includes a housing with the retaining part, the supply of secondary air to the flow direction of the secondary air in the inner part of the housing, the bumper plate, covered by a brace chassis and installed so that the bumper plate blocks the path of the secondary air containing a lot of impact channels passing through it;

the end cap contains many middle exhaust channels passing through it, and an air channel and a middle exhaust ports are mismatch, so that the secondary air discharged from the pneumatic channels, bumping into the end cap and flows through the middle exhaust ports for cooling the nozzle.

In a preferred embodiment of the secondary air nozzle suffers first loss of the total pressure when the flow through the air channels and the second loss of the total pressure when the flow through the middle exhaust ports, with the first pressure loss is larger than the second, so the second speed, moreover, the magnitude of the first speed is higher than the second. Preferably, the first pressure is at least about four times greater than the second pressure loss.

Optimal distribution of the secondary fuel injector according to the invention is preferably achieved by the fact that it contains a distribution chamber for the reception and distribution in space of the flow of secondary fuel, secondary fuel manifold, separated from the distribution chamber plate with holes having a number of holes for communication between the distribution chamber and the manifold, and a lot of fuel and exhaust channels along the perimeter, passing from the fuel manifold and through the housing for supplying secondary fuel into the combustion chamber.

Optimal supply of secondary air in the burner according to the invention is preferably achieved by the fact that the body of the nozzle contains a thickness in the radial direction of the rim portion with multiple air vent channels along the perimeter and passing through the rim portion, each of the air discharge channel has an input end which is connected with the duct feeding vtorichniye, located between the fuel outlet channels located on the perimeter.

The nozzle according to the invention can also contain a liner installed in the specified nozzle body having a hub with a Central hole, serving as a channel of the secondary air plate with holes passing between the hub and the housing of the nozzle and having multiple through holes, and an elongated portion of the hub, also running from the hub to the housing of the nozzle; a tube mounted radially between the hub and the housing of the nozzle and located at some distance from the plate with the holes in the axial direction of the containing hole to install the inlet pipe of the secondary fuel, secondary feed fuel to the nozzle; and a tube, the insert and the housing form an annular distribution chamber and the fuel reservoir with holes passing between the camera and the collector, and the specified body of the jet is equipped with placed along the perimeter of the outlet of the fuel channels passing from the fuel manifold and through the housing for supplying secondary fuel into the combustion chamber.

The task of the invention is solved by creating a nozzle unit fuel injector, the content is the form of a thickening in the radial direction of the rim, containing multiple air vent channels along the perimeter and passing through the rim portion, the housing also contains a breaker plate bounded by the retaining part with many of the cutting channels passing through the breaker plate; insert mounted in the housing coaxially with him and containing the hub, a plate with holes, protruding from the hub in the housing that contains many holes, and an elongated portion of the hub extending toward the tail end, also protruding from the hub to the casing, and the casing, a plate with holes and the elongated part of the hub to form an annular fuel manifold which is connected with the fuel outlet channels, located on the perimeter, and the housing has a Central opening forming a channel of the secondary air to the secondary air into the nozzle; a tube mounted radially between the hub and the housing and containing a hole to install the inlet pipe of the secondary fuel, secondary feed fuel to the nozzle and tube, plate with holes, the hub and the housing form an annular distribution chamber, chamber connected with the fuel reservoir through the holes in the plate; and an end roofs of the flow plate with education vozduhorazdelitelnoj camera, contains many middle exhaust channels, and middle exhaust ports and air ports are mismatch, so that the secondary air discharged from the pneumatic channels, bumping into the end cap and flows through the middle exhaust ports for cooling the nozzle.

In another embodiment, to allow the node according to the invention includes a housing, a feed channel of the secondary air flow direction of the secondary air in the inner part of the housing, the bumper plate, blocking the path of the stream of secondary air and has plenty of cutting channels through the plate, and an end cap that contains many middle exhaust channels passing through it, and an air channel and a middle exhaust ports are mismatch, so that the secondary air discharged from the pneumatic channels, bumping into the end cap and flows through the middle exhaust ports for cooling the nozzle.

The above-mentioned features, as well as the design and operation of the device made according to the invention, will become clearer in the light of the following description of a preferred variant implementation of the invention and the accompanying drawings.

Fig.2 depicts a nozzle in cross section, carried out along the line 2-2 in Fig.1.

Fig.3 shows in enlarged scale a transverse section of the nozzle release of fuel and air, located in the tail portion of the fuel injector shown in Fig.1.

Fig.4 depicts a view of the nozzle in the direction 4-4 of Fig.3, depicting the many outlets of the nozzle of the fuel injector.

Fig.5 shows the nozzle in cross-section on the line 5-5 of Fig.3, with the image plate with holes containing many holes.

Fig.6 shows the nozzle in cross section along the line 6-6 in Fig.3, with the image tube with a hole to install the inlet pipe of the secondary fuel.

Fig.7 shows the nozzle in cross section along the line 7-7 in Fig.3, depicting the impact plates with many pneumatic ports passing through the plate.

As shown in Fig.1 and 2, the fuel injector 10 with premixing, with the Central axis 12 passing in the longitudinal direction, includes the front end plate 14 and the tail (rear) end plate 16, and at least two arcuate cylindrical section 18, located in the axial direction between the end plastikverpackung openings forming the outlet plane 22 of the fuel injector, and end plates forming the mixing chamber 28, passing in the axial direction to the exhaust plane, in which fuel and air are mixed prior to combustion in the combustion chamber 30 located behind the outlet plane 22.

The cylindrical section 18 are located at some distance in the radial direction from the axis 12 of the nozzle, and each section has a radially inner surface 32 facing toward the center line of the fuel nozzle and forming the radially outer boundary of the mixing chamber. Each inner surface is a curved surface, and in particular - is the surface formed by the incomplete revolution around the respective axes of the sections (axes 34a, 34b) inside the mixing chamber. In this description, the expression "the surface formed by the incomplete turnover" means a surface formed by rotating a line less than one full turn around the Central lines 34a, 34b. Axis of the cylindrical sections are parallel to the center line of the fuel nozzle and radially equidistant offset from the specified center line, so that each adjacent pair of sections forming the air intake box 36 parallel to the Central line Vorskla 38 of the cylindrical section to the inner surface 32 adjacent cylindrical sections.

At least one, and preferably all of the cylindrical sections contain highway 40 fuel and distributed in the axial direction of the set being radially spaced fuel injection channels 42 for injection of the primary fuel, preferably gaseous fuel in a stream of primary air flowing into the mixing chamber.

The fuel injector also includes a Central component (box) 46, passing in the direction of the tail portion from the front end plate. The Central insert comprises a base 48, the nozzle 50 and the shell 52. The cowling is held in the axial direction from the base to the nozzle, forming a radially inner boundary of the mixing chamber 28 and the radially outer boundary of the duct 54 of the secondary air. The base 48 includes a number of channels of the secondary air, not shown in the drawings, the inlet of secondary air in the duct 54. The rear end 56 of the nozzle (shown in detail in Fig.3) made in the form of prohealthcare body of small aspect ratio, that is, it is made wide and has a flat or sloping rounded surface, and it is essentially aligned with the outlet plane 22.

Pipe 60 supply secondary fuel passes through the Central box shaped fuel. Thermocouples (not shown) installed in the slots 58 of thermocouples attached to the inner surface of the shell insert. The temperature signal provided by thermocouple that detects the presence of any flame within the mixing chamber, so that the automatic controller initiates the appropriate action adjustments, for example to temporarily change the amount of fuel.

As shown further in Fig.3-7, the nozzle 50 has a housing 62 containing a tubular shroud portion 64, passing in the axial direction from the front end 66 to radially enlarged rim 68 of the shroud tail end 70. Air exhaust ports 78, located on the perimeter, and fuel outlet ports 80, located on the perimeter, passing through the housing 62. As best seen in Fig.4, sixteen of the air channels along the perimeter, distributed circumferentially along with eight fuel outlet channels located on the perimeter, with equal angular intervals. Each air channel has an input end connected to the duct 54 of the secondary air, and an output end which is connected with the combustion chamber 30. The housing also includes a breaker plate 74, a limited bandage. Vosemnadcat includes a hub 84 with a Central hole, serving as a channel 86 of the secondary air inlet stream of secondary air from the feed duct 54 in the inner part of the nozzle, so that the bumper plate 74 stops the flow of secondary air. The plate 88 with holes containing sixteen holes 90, acts in the radial direction from the hub into the housing. Conical, widening in the direction of the elongated tail portion 94 of the hub protrudes from the hub into the housing. Casing, a plate with holes and the elongated part of the hub form a tubular fuel manifold 96 which is connected with the fuel outlet channels 80, located on the perimeter.

Tube 98 is installed radially between the hub 84 and the housing 62 and is located at some distance in the axial direction from the plate 88 with holes. The tube contains a hole 100 to the pipe 60 fuel supply for supplying a secondary fuel nozzle. Tube, housing, hub and plate with holes formed along the annular distribution chamber 102. Distribution chamber in the axial direction separated from the fuel manifold plate with holes, and the flow of fuel between the camera and the collector through Otley in the housing and located with a certain gap in the axial direction from the impact plates 74, forming a diffusion chamber 108. As best shown in Fig.3, middle exhaust ports are located on the mismatch of the flow relative to the bumper of the channels 76.

In the process, the flow of primary air enters the mixing chamber tangentially through the inlet window 36. The primary fuel flows through the channels 42 of the supply of primary fuel and enters the air stream is directed tangentially. The air stream carries the fuel in the mixing chamber 28 where the air and fuel to form a vortex flow around the insert 46 and be thoroughly and evenly mixed. Swirling fuel-air mixture flows through the outlet nozzle 20 and into the chamber 30 of the combustion chamber where it ignites and burns.

Meanwhile, the flow of secondary air flows through the duct 54 of the secondary air and enters the channel 86 to guide the secondary air in the inner part of the housing 62 of the nozzle. The secondary air is then expanded radially in the conical portion 87 of the channel 86, delayed breaker plate 74 and flows through the air channels 76. The air flow through the air channels experiences a pressure drop, so that the air exits from the ports in the Xia into the end cap 104, providing a shock cooling cap. Then the air flows through the middle channels 106 air release in the end cap 104 for evaporative cooling cap. Loss of pressure in the middle of the exhaust channels comprise only one quarter of the loss of pressure on the pneumatic ports. Accordingly, the air exits from the middle of the exhaust channels with a speed less than the speed of the shock jets. In the described embodiment, the median discharge channels are essentially parallel to the center line 12 of the fuel injector, however, the channels can be are inclined to increase the efficiency of cooling by evaporation.

The flow of secondary fuel flows from the pipe 60 fuel distribution chamber 102 and ultimately enters the combustion chamber 30 through the holes 90, the fuel manifold 96 and the channels 80 of the release of fuel, located on the perimeter. The holes provide a significant resistance to the flow of fuel so that the fuel becomes spatial (i.e., in the circumferential direction) is uniformly distributed in the distribution chamber 102 before passing into the reservoir 96 and the combustion chamber 30. If the plate 88 with holes was absent, Kahn is, the hen as channels located around the circumference at a distance from the feed pipe, would be the lack of fuel. The resulting uneven distribution of fuel in the combustion chamber would contribute to the formation of NOx.

Fuel injector made according to the present invention, has several advantages compared to more traditional nozzles, which nozzles air-fuel mixture are cooled solely by evaporation. When installing the turbine class 25 megawatts used to produce mechanical or electrical energy, the temperature of the end cap 38With lower than the end part of the insert from more traditional nozzles. Described nozzle reaches this temperature reduction when using about 55% of the smaller amount of cooling air than a conventional nozzle. Fewer cooling air provides moderate amounts of CO in combustion products (about 2 ppm) at full power turbine and a more significant reduction (about 30 parts per million or about 50%) at the level of about 80% of full power. In addition, the speed of the air leaving the middle exhaust any part, so the problems associated with aerothermochemical acoustic resonance, no, and prevents absorption of the flame in the mixing chamber.

Although the present invention has been shown and described with reference to a detailed embodiment of specialists in this field will understand that various changes in form and details of devices that are not beyond the scope of the invention specified in the attached claims.

Claims

1. Fuel injector for a combustor of a gas turbine plant comprising at least two arcuate cylindrical sections, each of which has an axis located essentially parallel to the Central axis of the nozzle and radially displaced from it, and the cylindrical section to form a radially outer boundary of the mixing chamber, each adjacent pair of cylindrical sections also forms the inlet box, inlet flow of primary air into the mixing chamber, at least one of the cylindrical sections contains distributed in the axial direction of the channels of the fuel injection of the primary fuel into the stream of primary air; Central insert, contains about the ka forms a radially inner boundary of the mixing chamber and the radially outer boundary of the duct of the secondary air and said nozzle includes a housing containing the retaining portion; the channel of the secondary air to flow direction of the secondary air to the interior of the housing; a breaker plate, covered by the tire casing, so that the bumper plate shall suspend the period of the secondary air contains many cutting channels passing through it; and the end cap containing many middle exhaust channels passing through it, and an air channel and a middle exhaust ports are mismatch, so that the secondary air discharged from the pneumatic channels, bumping into the end cap and flows through the middle exhaust ports for cooling the nozzle.

2. Fuel injector under item 1, characterized in that the secondary air suffers first loss of the total pressure when the flow through the air channels and the second loss of the total pressure when the flow through the middle exhaust ports, with the first pressure loss is larger than the second, so that the secondary air strikes into the end cap from the first speed in and out of the middle of the channel with the second speed, and the value of the first speed is higher than the second.

3. Fuel injector under item 2, characterized in that PNA nozzle on one of the PP.1-3, characterized in that it contains a distribution chamber for the reception and distribution in space of the flow of secondary fuel, secondary fuel manifold, separated from the distribution chamber plate with holes having a number of holes for communication between the distribution chamber and the manifold; and many of the fuel discharge channel along the perimeter, passing from the fuel manifold and through the housing for supplying secondary fuel into the combustion chamber.

5. Fuel injector under item 4, characterized in that the nozzle body contains the thickness in the radial direction of the rim portion with multiple air vent channels along the perimeter, and passing through the rim portion, each of the air discharge channel has an input end which is connected with the duct of the secondary air, and an output end which is connected with the combustion chamber, and air channels located around the perimeter, located between the fuel outlet channels located on the perimeter.

6. Fuel injector on one of the PP.1-5, characterized in that the secondary fuel is a gaseous fuel.

7. Fuel fo the, aderrasi hub with a Central hole, serving as a channel of the secondary air plate with holes passing between the hub and the housing of the nozzle and having multiple through holes, and an elongated portion of the hub, also running from the hub to the housing of the nozzle; a tube mounted radially between the hub and the housing of the nozzle and located at some distance from the plate with the holes in the axial direction of the containing hole to install the inlet pipe of the secondary fuel, secondary feed fuel to the nozzle; and the tube, the insert and the housing form an annular distribution chamber and the fuel reservoir with holes, passing between the camera and the collector, and the specified body of the jet is equipped with placed along the perimeter of the outlet of the fuel channels passing from the fuel manifold and through the housing for supplying secondary fuel into the combustion chamber.

8. Fuel injector under item 7, characterized in that the nozzle body contains the thickness in the radial direction of the rim portion with multiple air vent channels along the perimeter and passing through the rim portion, each of the air discharge channel has an input canaricam air channels, located on the perimeter, placed between the fuel outlet channels located on the perimeter.

9. Fuel injector under item 7 or 8, characterized in that the secondary fuel is a gaseous fuel.

10. Fuel injector on one of the PP.1-9, characterized in that the medial channels are essentially parallel to the center line of the nozzle.

11. To allow the node to the fuel injector, comprising a housing with a retaining part having a front end and a tail end, and the tail end is made in the form of a thickening in the radial direction of the rim, containing multiple air vent channels along the perimeter and passing through the rim portion, the housing also contains a breaker plate bounded by the retaining part with many of the cutting channels passing through the breaker plate; insert mounted in the housing coaxially with him and containing the hub, a plate with holes, protruding from the hub in the housing that contains many holes, and an elongated portion of the hub, extending towards the tail end, also protruding from the hub to the casing, and the casing, a plate with holes and the elongated part of the hub form Colm housing has a Central hole, forming the channel of the secondary air to the secondary air into the nozzle; a tube mounted radially between the hub and the housing and containing a hole to install the inlet pipe of the secondary fuel, secondary feed fuel to the nozzle and tube, plate with holes, the hub and the housing form an annular distribution chamber, chamber connected with the fuel reservoir through the holes in the plate; and an end cover, a limited tail end of the housing and located at a certain distance in the axial direction from the bumper plate with the formation of the air-distributing chamber, containing many middle exhaust channels, and middle exhaust ports and air ports are mismatch, so that the secondary air discharged from the pneumatic channels, bumping into the end cap and flows through the middle exhaust ports for cooling the nozzle.

12. To allow the node to the fuel injector, comprising a housing; a supply channel of the secondary air flow direction of the secondary air to the interior of the housing; a breaker plate, blocking the path of the stream of secondary air and has plenty of impact channels passing through p is trainie channels and middle exhaust ports are mismatch, so that the secondary air discharged from the pneumatic channels, bumping into the end cap and flows through the middle exhaust ports for cooling the nozzle.

 

Same patents:

The invention relates to the field of energy and can be used in devices for fuel combustion, mainly in gas turbine engines and in the process furnace devices

The invention relates to a device controlling the feed of fuel to the main combustion chamber of the CCD in the fuel injector

The invention relates to gas turbine engines, particularly aircraft and stationary power installations

The invention relates to a stationary gas turbine engines, in particular for low-emission combustion chambers

FIELD: gas-turbine plants.

SUBSTANCE: proposed method includes changing of fuel rate depending on power by metering out delivery of fuel into manifolds of coaxially installed pilot and main burners of burner assemblies with preliminary mixing of fuel and air. Burner assemblies are installed in two tiers, and fuel is delivered into burners of both tiers. At starting fuel is fed into manifold of pilot burners of outer tier and before idling, into manifold of pilot, burners of inner tier. At idling amount of fuel fed into pilot burners of outer and inner tiers is maintained equal. Then fuel delivery into pilot burners of outer and inner tiers is increased. Prior to operation under no-load conditions fuel is fed to main burners of outer and inner tiers. In the range from no-load to rated load, fuel delivery into main burners is increased with simultaneously decreasing relative portion of fuel fed through pilot burners. Invention provides reduction of content of nitrogen oxides NOxin exhaust gases of gas-turbine plant.

EFFECT: provision of stable burning of lean mixtures under any operating conditions.

4 cl, 2 dwg

FIELD: gas-turbine engines.

SUBSTANCE: proposed fuel-air burner has fuel injector in the form of body with fuel feed and spray holes as well as axial- and tangential-flow air swirlers, air flow regulator disposed between rear side of injector body and inlet end of axial-flow swirler that forms slit duct together with its inlet end. Axial- and tangential-flow air swirlers are made in the form of open-end channels accommodating blades and each is provided with converging-diverging nozzle having internal and external channel walls. External channel wall of converging part of axial-flow swirler nozzle has curvature inverse relative to internal channel wall of tangential-flow swirler nozzle. Diverging part of axial-flow swirler is made in the form of cone whose vertex is disposed upstream of nozzle critical section. Angle between burner axis and generating line of cone is 30 to 90 deg. Critical section of axial-flow swirler converging-diverging nozzle is disposed upstream of point of intersection between external channel wall and fuel spray cone generating line.

EFFECT: reduced emission of pollutants in exhaust gases, improved starting characteristics and fuel economic efficiency, enhanced reliability of combustion chamber.

1 cl, 2 dwg

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: proposed gas-turbine engine has central stage arranged in gas duct of engine from its part arranged higher relative to direction of main gas flow to part lower in direction of main gas flow and provided with exhaust gas cone forming device in direction of main gas flow, and guide arrangement. Gas-turbine engine has group of blades, group of fuel nozzles and group of igniters. Guide arrangement is located in zone of edge of exhaust gas cone-forming device arranged higher relative to direction of main gas flow. Group of blades is located in gas duct out of the limits of central stage. Blades are provided with atomizing guides extending through blades. Fuel nozzles are installed on inner ends of corresponding atomizing guides. Each nozzle is provided with input, output and passage between input and output. Passage has part arranged to direct fuel flow to first part of passage surface located across and widening downwards in direction of flow with subsequent deflection fuel flow by first part of surface and its outlet from nozzle. Igniters are arranged in corresponding atomizing guides for igniting fuel from corresponding fuel nozzle.

EFFECT: provision of reliable lighting up in afterburner, improved recirculation of fuel in flow.

13 cl, 8 dwg

FIELD: fuel systems.

SUBSTANCE: the fuel-injection nozzle for a turbo-machine combustion chamber outfitted with two fuel-injection nozzle units has the first fuel-supply tube, connected to which is an annular nozzle end for injection of primary fuel into the combustion chamber, the second fuel-supply tube that envelops the mentioned first tube, and connected to which is a cylindrical extension piece for injection of secondary fuel into this combustion chamber. The extension piece has an annular groove, whose diameter exceeds the diameter of the mentioned second fuel supply tube and runs over its entire length. The third tube is provided that envelop the second tube, an connected to which is a tubular separating component introduced in the mentioned annular groove of the cylindrical extension piece in such a way that two annular cavities are formed, in which the cooling agent can circulate up to the end of the fuel-injection nozzle within 360 degrees in the whole cross-section of the mentioned cavities.

EFFECT: provided protection of the fuel systems, prevented clogging of the fuel-injection nozzles with coke due to effective cooling without considerable variations of the nozzle overall dimensions.

8 cl, 3 dwg

FIELD: fuel systems.

SUBSTANCE: the device for supply of fuel to the combustion chamber has at least one main nozzle and one preliminary-injection nozzle, pump, the first actuator valve installed in the first pipe-line connected to the preliminary-injection nozzle, the second actuator valve used for control of fuel consumption in the secondary pipe-line connected to the preliminary-injection nozzle through the first actuator valve rated at a lower consumption rate. The first pipe-line is also connected to the main nozzle for control of consumption of fuel supplied to the nozzle by the first actuator valve, provision is made for a direction- selecting valve installed past the first valve, and an intermediate line connecting the first and second lines that are used for fuel supply to the main nozzle and/or to the preliminary-injection nozzle.

EFFECT: provided stable fuel supply to the combustion chamber.

8 cl, 2 dwg

FIELD: continuous combustion chambers using liquid or gas fuel.

SUBSTANCE: fuel nozzle comprises first valve that closes when the pressure of inflowing fuel reaches a given value and second batching valve mounted at the outlet of the first valve, which is opened under the action of the second given value of fuel pressure. The second valve is open when the pressure increases so that to provide the inflow of fuel to the consumers. The batched fuel flow rate is a function of the flowing sections of the openings made at the level of the second valve. The nozzle is additionally provided with means for individual adjusting of the second threshold value of pressure made so that to provided the uniform injection of fuel to the combustion chamber.

EFFECT: expanded functional capabilities.

4 cl, 6 dwg

FIELD: continuous combustion chambers.

SUBSTANCE: combustion chamber comprises hollow cylindrical housing whose wall receive scroll and air radial swirlers with blades that provide swirling in opposite directions, shells, bushings mounted for permitting movement in radial direction, branch pipe, swirling chambers, and nozzle. Each combined nozzle has centrifugal nozzle whose outer side is in a contact with inner side of the bushing and jet nozzle with cylindrical housing mounted coaxially in the inner space of the branch pipe between the outer wall of the housing of the jet nozzle and inner wall of the branch pipe. The outlet section of the housing of the jet nozzle is bent to the passage of the scroll spiral of the radial swirler. The outlet section of the jet nozzle is parallel to the wall of the inlet section of the branch pipe and is at a distance of 0.8-1.2 of the diameter of the jet nozzle housing from it.

EFFECT: reduced hydraulic drag and oxides emission.

9 dwg

FIELD: engine engineering.

SUBSTANCE: method comprises filling with solder the radial spaces made in the ring nozzle tip provided with the first nozzle openings for injecting primary fuel and in the cylindrical nozzle that embraces the ring nozzle tip and has second nozzle openings for injecting secondary fuel, setting the ring nozzle tip inside the cylindrical nozzle, mounting both of the members on the first fuel supply pipe for primary fuel and second fuel supply pipe for secondary fuel that embraces the first pipe and on the outer wall of the fuel nozzle, and setting the nozzle spryer assembled into the chamber where it is heated to provide adhesion of the members with solder.

EFFECT: expanded functional capabilities and eased assembling.

6 cl, 7 dwg

FIELD: gas-turbine engine engineering.

SUBSTANCE: ring combustion chamber comprises fire tube and vortex burners arranged over periphery of its face and made of fuel-air scroll and air swirlers with outlet conical branch pipe having cylindrical section. The shell is secured to the face coaxially to each branch pipe defining a ring space. The outer side of the end cylindrical section or inner side of the shell located above it is provided with longitudinal ribs distributed uniformly over periphery and defining insulated passages. The through openings connected with the ring space are made in the face of the fire tube under the shell.

EFFECT: enhanced reliability and expanded functional capabilities.

2 cl, 2 dwg

FIELD: gas-turbine engine engineering.

SUBSTANCE: method comprises separating the fuel supply through small fuel nozzle from that through high-flow rate nozzle, with controllable fuel supply realized directly in the device. The device comprises outer housing, high-flow rate nozzle made of outer housing of the small fuel nozzle and secured to it, piston-slide valve, and spring, interposed between the outer housings of the device and high-flow rate nozzles provided with the passages for fuel supply. The fuel supply is controller by opening passages for supplying fuel to the small nozzle and closing the passages for supplying fuel to the high-flow rate nozzle. When the pressure of fuel increases, the passages for supplying fuel to the high-flow rate nozzle are opened, and the passages for supplying fuel to the small nozzle are simultaneously closed.

EFFECT: enhanced efficiency.

2 cl, 5 dwg

Up!