CN106524223B - Combustion chamber with main nozzle assembly and mini-nozzle assembly - Google Patents
Combustion chamber with main nozzle assembly and mini-nozzle assembly Download PDFInfo
- Publication number
- CN106524223B CN106524223B CN201611163961.XA CN201611163961A CN106524223B CN 106524223 B CN106524223 B CN 106524223B CN 201611163961 A CN201611163961 A CN 201611163961A CN 106524223 B CN106524223 B CN 106524223B
- Authority
- CN
- China
- Prior art keywords
- micro
- nozzle
- fuel injection
- main
- fuel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
Abstract
A combustion chamber with a main nozzle assembly and a micro nozzle assembly, the combustion chamber comprising a diffuser, a main nozzle assembly, a micro nozzle assembly, a flame tube and a combustion chamber casing, wherein the front end of the flame tube is provided with the main nozzle assembly and the micro nozzle assembly; the micro nozzle assembly comprises a plurality of micro nozzles, the outer diameter of each micro nozzle is 3-15 mm, and the center distance between adjacent micro nozzles is 1.1-2 times of the outer diameter of each micro nozzle; the miniature nozzle component comprises a plurality of matching rings, the number of the matching rings is equal to that of the main nozzles of the main nozzle component, and the main nozzles of the main nozzle component are assembled in the matching rings. The invention can be applied to gas turbines, aeroengines and boilers, and the combustion chamber comprises four fuel injection modes of front-end fuel injection, main premixed fuel injection, diffusion fuel injection and micro premixed fuel injection, thereby being beneficial to realizing high-efficiency combustion organization and flexible working condition adjustment while keeping low emission.
Description
Technical Field
The present invention relates to a burner, and in particular to a combustion chamber with a main nozzle assembly and a micro nozzle assembly, and a gas turbine, an aeroengine and a boiler employing the same.
Background
The gas turbine is an important power device for converting chemical energy into mechanical energy, and has wide application in the aspects of distributed energy sources, pipeline transportation, emergency power sources, ship power and the like. An important model of the gas turbine is modified from an aeroengine, and compared with an internal combustion engine, the aeromodified gas turbine has the advantages of light weight, small volume, quick starting, high efficiency and the like. Technical routes for aero-engine retrofit ground gas turbines are generally: the fan of the turbofan engine is cut off, the fuel combustion chamber is changed into a gas combustion chamber, the tail nozzle is omitted, the power turbine output power is increased, and a corresponding auxiliary machine system is increased or modified. The technical route has a successful case at home and abroad. The main technical difficulty faced in retrofitting aircraft engines to ground gas turbines today is the low pollution retrofitting of the combustion chamber. The transformation from the aero-engine to the ground gas turbine changes the aero-engine from thrust output to electric or power output, and changes the technical standard which the final product needs to meet. After the change to the ground gas turbine, the related national standards for the ground gas turbine must be met, and the foremost among these are environmental standards for pollutant emissions of the gas turbine.
Meanwhile, due to the fact that environmental problems are increasingly serious, haze, acid rain and the like are frequently generated, and life of people is seriously influenced. The country has established strict standards for controlling emissions from pollutant-producing combustion equipment such as boilers, gas turbines, aeroengines, etc., older equipment that does not meet the standards will be gradually eliminated and new equipment will not be allowed to come into the market. Currently, the main pollutant emissions of combustion equipment such as gas turbines are carbon monoxide (CO), nitrogen Oxides (NO) X ) And Unburned Hydrocarbons (UHC). Wherein the emissions of CO and UHC have met the relevant national standards through technological advancement, and the emissions requiring strict control are NO X 。NO X The generation mechanism of (a) comprises: thermal, rapid and fuel types, wherein the thermal mechanism is the current combustion device to produce NO X Is a major mechanism of (a). Thermal NO X From the reaction of nitrogen with oxygen in air in a high temperature environment, thus reducing NO X The main measure of (2) is to reduce the temperature of the flame in the combustion process, and the common measure is to use premixed combustion.
Typical premix combustion equipment such as gas turbine low emission combustors have to increase the length of the fuel and air premixing section in order to achieve adequate premixing of fuel and air; in order to stabilize the premixed flame, the combustion space needs to be increased, so that the volume of the combustor flame tube is increased; the addition of a resonant cavity or the like is also required to control premixed combustion oscillations, resulting in a cumbersome and complex overall combustor structure. At the same time, the combustion control and adjustment are complex, and a plurality of regulating valves and pipelines are needed to be added. Such combustion techniques have a number of drawbacks, both for boilers and gas turbines. In particular, for gas turbines retrofitted from aeroengines, due to the compact structure of the aeroengines themselves, the limited space of the combustion chamber, the amount of retrofitting effort required by the application of the prior art is great, and problems of complex control, difficult regulation, etc. remain.
Disclosure of Invention
In view of the above, a primary object of the present invention is to provide a combustion chamber, and a gas turbine, an aeroengine and a boiler using the same, so as to solve at least one of the above problems.
In order to achieve the above object, as one aspect of the present invention, the present invention discloses a combustion chamber with a main nozzle assembly and a micro nozzle assembly, comprising a diffuser, a main nozzle assembly, a micro nozzle assembly, a flame tube and a combustion chamber casing, wherein the diffuser is arranged at the end of the combustion chamber casing, and is used for reducing speed and diffusing high-temperature and high-pressure air entering the combustion chamber; the flame tube is arranged in the combustion chamber casing, and a part of air enters the flame tube through the cooling holes on the surface of the flame tube wall to cool the high-temperature part of the flame tube; the method is characterized in that:
the front end of the flame tube is provided with the main nozzle assembly and the micro nozzle assembly, and most of air entering through the diffuser pipe is mixed with injected fuel through air channels of the main nozzle assembly and the micro nozzle assembly and then burnt in the flame tube;
the micro nozzle assembly comprises a fuel main pipe and N micro nozzle units, wherein N is a natural number, and the fan-shaped included angle beta of the micro nozzle units and the number N of the micro nozzle units meet the condition that Nxbeta=360; the micro nozzle unit comprises a plurality of micro nozzles, wherein the outer diameter of each micro nozzle is 3-15 mm, and the center distance between adjacent micro nozzles is 1.1-2 times of the outer diameter of each micro nozzle; and
the miniature nozzle unit comprises a plurality of matching rings, the number of the matching rings is equal to that of main nozzles of the main nozzle assembly, and the main nozzles of the main nozzle assembly are assembled in the matching rings.
As another aspect of the invention, a gas turbine, an aeroengine and a boiler employing a combustion chamber as described above are also disclosed.
Based on the technical scheme, compared with the existing premixed combustion technology, the premixed combustion technology has the following advantages: (1) The main structure of the gas turbine is slightly changed, and the method is particularly suitable for aero-retrofit gas turbines; (2) The fuel is injected by the micro nozzle, the fuel and the air are fully mixed, lower combustion emission is easy to achieve, and the emissions of CO and NO in the combustion chamber X Can be lower than 25ppm@15% O 2 Meets the national standard requirements of GB13223 and the like; (3) The multi-path fuel classification can realize flexible combustion adjustment; (4) The adoption of the front-end fuel injection effectively suppresses combustion oscillation problems faced by premixed combustion.
Drawings
FIG. 1 is a schematic view of a combustion chamber with primary and micro nozzles according to the present invention;
FIG. 2 is a cross-sectional view taken along line A-A of FIG. 1;
FIG. 3 is a schematic view of the main nozzle structure of the combustion chamber of the present invention;
FIG. 4 is a cross-sectional view taken along line C-C of FIG. 3;
FIG. 5 is a three-dimensional cross-sectional view of the primary nozzle shown in FIG. 3;
FIG. 6 is a schematic illustration of an arrangement of a micro-nozzle assembly of the combustor of the present invention;
FIG. 7 is a schematic illustration of a single micro-nozzle structure in the micro-nozzle assembly shown in FIG. 6;
FIG. 8 is a cross-sectional view B-B of FIG. 7;
FIG. 9 is a schematic three-dimensional cross-sectional view of a micro-nozzle assembly of the present invention;
FIG. 10 is a three-dimensional cross-sectional view of a combustion chamber with primary and micro-nozzles of the present invention;
fig. 11 is a schematic structural diagram of an application of the technical scheme of the present invention in a branched tubular combustion chamber.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to the accompanying drawings, but the present invention is not limited to the scope of the embodiments.
The invention discloses a combustion chamber with a main nozzle assembly and a micro nozzle assembly, which comprises a diffuser, the main nozzle assembly, the micro nozzle assembly, a flame tube and a combustion chamber casing, wherein the diffuser is arranged at the end part of the combustion chamber casing and used for diffusing high-temperature high-pressure air entering the combustion chamber in a speed reducing manner; the flame tube is arranged in the combustion chamber casing, the front end of the flame tube is provided with a main nozzle assembly and a micro nozzle assembly, and most of air entering through the diffuser pipe is mixed with injected fuel through air channels of the main nozzle assembly and the micro nozzle assembly and then is combusted in the flame tube; and the rest part of air enters the flame tube through the cooling holes on the surface of the flame tube wall to cool the high-temperature part of the flame tube.
The micro nozzle assembly comprises a fuel main pipe and N micro nozzle units, wherein N is a natural number, and the fan-shaped included angle beta of the micro nozzle units and the number N of the micro nozzle units meet the condition that Nxbeta=360; the micro nozzle unit comprises a plurality of micro nozzles, wherein the outer diameter of each micro nozzle is 3-15 mm, and the center distance between adjacent micro nozzles is 1.1-2 times of the outer diameter of each micro nozzle; and
the miniature nozzle unit comprises a plurality of matching rings, the number of the matching rings is equal to that of the main nozzles of the main nozzle assembly, and the main nozzles of the main nozzle assembly are assembled in the matching rings.
Preferably, the combustion chamber further comprises a pilot fuel injection assembly positioned between the diffuser and the main nozzle assembly, the pilot fuel injection assembly comprising a pilot fuel injection tube for injecting pilot fuel into the high-speed airflow after the diffuser for rapid mixing with air to inhibit combustion oscillations.
Preferably, the fuel injection direction of the front-end fuel injection assembly forms an included angle of 60-120 degrees with the air flow direction discharged by the diffuser, and the preferable value is 90 degrees;
the front fuel injection pipe is an annular circular pipe with fuel injection holes and is fixed on the wall surface of the casing behind the diffuser through a connector pipe.
Preferably, the main nozzle assembly includes a dual channel nozzle stem, a fuel distributor, and a main nozzle; wherein the dual channel nozzle stem includes two fuel channels for respectively inputting main premixed fuel and diffusion fuel. The main nozzle consists of fuel injection blade, swirl blade, central blunt body, fuel partition board, nozzle casing, etc.
Preferably, structural parameters of the main nozzle assembly are satisfied:
k/h=1.5 to 2.5, preferably 2; wherein K is the inner diameter of the nozzle casing, and H is the outer diameter of the central blunt body;
l/k=0.3 to 0.8, preferably 0.5; wherein L is the distance between the end face of the central blunt body and the end face of the nozzle casing;
the included angle between the swirl vane and the central line of the central blunt body is 20-60 degrees, and the preferable value is 35 degrees;
the included angle between the fuel injection hole and the central line of the central blunt body is 10-60 degrees, and the preferable value is 45 degrees;
each two-channel nozzle bar is connected to at least one main nozzle and a corresponding fuel distributor.
Preferably, the micro-nozzle comprises a central body, micro-swirl vanes arranged around the central body and a micro-nozzle casing surrounding the micro-swirl vanes, wherein the micro-nozzle casing comprises 1-8 micro-fuel injection holes;
preferably, the front end of the central body is of a streamline structure;
preferably, the number of micro cyclone blades in the micro nozzle is 2-12;
preferably, the ratio of the outer diameter of the central body to the inner diameter of the micro nozzle casing is 0.2-0.6, and the preferable value is 0.5;
preferably, the micro-nozzle is fixed between the front cover and the rear cover of the micro-nozzle unit, and the fuel injection hole contained in the micro-nozzle cartridge in the micro-nozzle is contained in a space formed by the front cover, the rear cover and the housing of the micro-nozzle group.
Preferably, the flame tube consists of two concentric rings; the front end of the flame tube is connected with the inner arc surface and the outer arc surface of the micro nozzle shell in the micro nozzle assembly; the outer wall surface of the flame tube is fixed on the combustion chamber outer casing, and the rear end of the flame tube is lapped on the turbine inlet section of the gas turbine;
preferably, the cooling of the flame tube adopts one or a combination of film cooling, rib cooling and divergent cooling.
Preferably, the fuel injection mode of the combustion chamber includes at least one of a pilot fuel injection, a main premixed fuel injection, a diffusion fuel injection and a micro premixed fuel injection.
Preferably, the combustion chamber is an annular, branched, annular or single-tube combustion chamber.
The invention also discloses a gas turbine, an aeroengine and a boiler comprising the combustion chamber.
As a preferred embodiment of the present invention, the present invention discloses a combustion chamber comprising: diffuser, front-end fuel injection assembly, main nozzle assembly, micro-nozzle assembly, combustor basket, and the like, wherein:
the main nozzle assembly comprises a double-channel nozzle rod, a nozzle mounting seat, a fuel distributor, a main nozzle and a main nozzle, wherein the main nozzle consists of a fuel injection blade, a swirl blade, a front end of a central blunt body, a fuel separation plate, a nozzle casing and the like; and
the micro nozzle assembly consists of a fuel main pipe, a micro nozzle unit and the like, wherein the micro nozzle unit consists of a micro nozzle, a micro nozzle unit fuel inlet, a fuel uniform distributor, a micro nozzle unit shell, a micro nozzle unit front cover, a micro nozzle unit rear cover, a matching ring and the like;
the front fuel injection assembly consists of a front fuel injection pipe, a connector pipe, a mounting seat and the like, wherein the fuel injection direction forms an included angle of 60-120 degrees with the air flow direction discharged by the diffuser, and the preferable value is 90 degrees.
In the combustion chamber, the main nozzle assembly comprises a main premixing and diffusion two-way fuel pipeline, and the structural parameters of the main nozzle assembly are as follows: k/h=1.5 to 2.5, preferably 2; l/k=0.3 to 0.8, preferably 0.5; the included angle between the swirl vane and the central line of the central blunt body is 20-60 degrees, and the preferable value is 35 degrees; the included angle between the fuel injection hole and the central line of the central blunt body is 10-60 degrees, and the preferable value is 45 degrees; each two-channel nozzle bar is connected to at least one main nozzle and a corresponding fuel distributor.
In the combustion chamber, the micro nozzle assembly comprises N (N is more than or equal to 1) micro nozzle units, wherein the fan-shaped included angle beta of the micro nozzle units and the number N of the micro nozzle units meet the condition that Nxbeta=360; the micro nozzle unit comprises the same number of matching rings as the main nozzles of the main nozzle assembly; the micro nozzle unit comprises a plurality of micro nozzles, wherein the outer diameter of each micro nozzle is 3-15 mm, and the center distance between adjacent micro nozzles is 1.1-2 times of the outer diameter of each micro nozzle.
The micro nozzle comprises a central body, micro swirl vanes, a micro nozzle casing and the like, wherein the micro nozzle casing comprises 1-8 micro fuel injection holes, and the front end of the central body is of a streamline structure; the number of the micro-swirl blades in the micro-nozzle is 2-12, the ratio of the outer diameter of the central body to the inner diameter of the micro-nozzle casing is 0.2-0.6, and the preferable value is 0.5; the micro-nozzle is fixed between the front cover and the rear cover of the micro-nozzle unit, and fuel injection holes contained in the micro-nozzle cartridge receiver in the micro-nozzle are contained in a space formed by the front cover, the rear cover and the housing of the micro-nozzle unit.
In the combustion chamber, the flame tube mainly consists of two concentric rings. The front end of the flame tube is connected with the inner arc surface and the outer arc surface of the micro nozzle shell in the micro nozzle assembly; the outer wall surface of the flame tube is fixed on the combustion chamber outer casing through a pin, and the rear end of the flame tube is lapped on the turbine inlet section of the gas turbine. The wall surface of the flame tube can adopt a cooling mode of air film cooling, rib cooling, divergent cooling and the like and a combined cooling mode.
The preferred combination of combustion chambers includes four fuel injection modes including pilot fuel injection, main premixed fuel injection, diffusion fuel injection and micro premixed fuel injection, but these four fuel injection modes are not necessarily included in the application at the same time.
The invention also discloses equipment such as a gas turbine, an aeroengine, a boiler and the like, which comprise the combustion chamber with the micro nozzle.
Specific embodiments of the present invention are described further below with reference to the accompanying drawings.
Referring to fig. 1 and 2, the present invention discloses a low emission combustor with a main nozzle 320 and a micro nozzle 420, which includes a diffuser 1, a pilot fuel injection assembly 2, a main nozzle assembly 3, a micro nozzle assembly 4, a liner 5, a combustor casing (a combustor casing 6 and a combustor casing 7), and the like. In particular, a fuel injection mode using a combination of the main nozzle 320 and the micro nozzle 420 is adopted, and a specific fuel injection is realized through the main nozzle assembly 3 and the micro nozzle assembly 4.
The low emission combustor of the present invention is a primary component of a gas turbine that functions to convert chemical energy of fuel into thermal energy and reduce the generation of pollutants during combustion. After the high-temperature high-pressure air discharged from the gas turbine compressor is subjected to speed-reducing diffusion through the diffuser 1, most of the air enters the air channels in the main nozzle assembly 3 and the micro nozzle assembly 4, is mixed with the corresponding injected fuel, and is combusted at the downstream of the main nozzle 320 and the micro nozzle 420. The other part enters the flame tube through the cooling holes on the wall surface of the flame tube 5 to cool the high-temperature part of the flame tube, so that the flame tube is prevented from being ablated at high temperature. As shown in fig. 2, 6, 10, and 11, the present invention is unique in that a combination of the main nozzle 320 and the micro nozzle 420 is used to achieve flexible combustion organization and adjustment. The fuel in the combustion chamber is divided into four types according to the action: pre-fuels, main premix fuels, diffusion fuels, and micro premix fuels. The front-end fuel is injected into the high-speed airflow after the diffuser 1 through the front-end fuel injection assembly 2, is quickly mixed with air, and mainly plays a role in inhibiting combustion oscillation. The premixed fuel and the micro-premixed fuel are fully mixed with air through the main nozzle assembly 3 and the micro-nozzle assembly 4, so that premixed combustion is realized, the high-temperature combustion area is reduced, and NO is reduced x And the purpose of pollutant discharge. Diffusion combustion through diffusion tube in main nozzle assembly 3The flame stabilizing agent is sprayed into the main combustion area of the combustion chamber, and mainly plays a role in stabilizing flame under the ignition and low working conditions of the combustion chamber.
As shown in fig. 3-5, the main nozzle assembly 3 according to the present invention includes a dual channel nozzle stem 302, a nozzle mount 301, a fuel distributor 303, and a main nozzle 320, wherein the main nozzle 320 is composed of a fuel injection vane 321, a swirl vane 323, a central blunt body front end 311, a central blunt body 319, a fuel partition plate 314, a nozzle casing 316, and the like, as shown in fig. 3-5. The fuel injected through the main nozzle assembly 3 is divided into two types: primary premix fuel and diffusion fuel. The main premixed fuel enters the channel 307 in the fuel distributor 303 through the channel 305 in the double-channel nozzle rod 302, passes through the opening of the nozzle casing 316 corresponding to the installation position of the fuel injection blade 321, enters the fuel injection blade 321, namely the channel 325, and is injected into the air from the diffuser 1 through the fuel injection holes 322 on the fuel injection blade 321, and is mixed with the air to form the combustible mixture. Diffusion fuel is also fed from the dual channel nozzle stem 302 through another channel 304 in the dual channel nozzle stem 302 into the channel 306 in the fuel distributor 303, through openings in the nozzle casing 316 corresponding to the mounting location of the swirl vanes 323 into the swirl vanes 323, i.e. into the channels 324, and then into the annular channel 315 in the central bluff body 319, from the fuel injection holes 317 at the end face of the central bluff body 319, for mixed combustion with air rotationally directed through the swirl vanes 323. The diffusion fuel is mainly used when the combustion chamber ignites and is in a low working condition, and the diffusion fuel is closed after combustion is stable and in a high working condition. The following relationships between the structural parameters in the main nozzle assembly 3 are satisfied (see fig. 4, 5): (1) k/h=1.5 to 2.5, preferably 2; (2) l/k=0.3 to 0.8, preferably 0.5; (3) the included angle between the swirl vane 323 and the central line of the central blunt body 319 is 20 degrees to 60 degrees, and the preferable value is 35 degrees; (4) the fuel injection hole 317 forms an angle of 10 degrees to 60 degrees with the center line of the central blunt body 319, preferably 45 degrees; (5) each dual channel nozzle stem 302 connects at least one primary nozzle and a corresponding fuel distributor 303.
The micro-nozzle assembly 4 according to the present invention includes a fuel manifold 401, an interface 402 thereof, a micro-nozzle unit 430, etc., wherein the micro-nozzle unit 430 is composed of a micro-nozzle 420, a micro-nozzle unit fuel inlet 412, a fuel distributor 413, a micro-nozzle unit housing 411, a micro-nozzle unit front cover 414, a micro-nozzle unit rear cover 415, a mating ring 416, etc., as shown in detail in fig. 1-2 and fig. 6-9. Fig. 6 and 9 show a front view and a partial cross-sectional view of the micro nozzle unit 430. The micro-nozzle assembly 4 comprises N (N.gtoreq.1) micro-nozzle units 430, wherein the micro-nozzle units 430 are fan-shaped (see FIG. 6), wherein the fan-shaped included angle β and the number of micro-nozzle units N satisfy Nxβ=360. The micro nozzle unit 430 includes at least one mating ring 416 that is equal in number to the number of main nozzles 320 included in the main nozzle assembly 3. The micro nozzle unit 430 includes a plurality of micro nozzles 420, and the micro nozzles 420 fill the space formed by the mating ring 416 and the micro nozzle unit housing 411, and meet the requirements of the outer diameter and the spacing of the micro nozzles 420. The outer diameter of the micro nozzle 420 is 3-15 mm, and the center distance between adjacent micro nozzles 420 is 1.1-2 times of the outer diameter of the micro nozzle 420. The micro nozzle 420 includes a central body 423, micro swirl vanes 424, a micro nozzle casing 422, etc., wherein the micro nozzle casing 422 contains 1-8 micro fuel injection holes 421, and a front end 425 of the central body 423 has a streamline structure, as shown in fig. 7 and 8. The micro nozzle 420 includes 2 to 12 micro swirl vanes 424, and the ratio of the outer diameter of the central body 423 to the inner diameter of the micro nozzle case 422 is 0.2 to 0.6. The micro nozzle 420 is fixed between the front cover 414 and the rear cover 415 of the micro nozzle unit, and the fuel injection holes 421 contained in the micro nozzle 422 in the micro nozzle 420 are contained in the space formed by the front cover 414, the rear cover 415, and the housing 411 of the micro nozzle group. A fuel manifold 401 is connected to each of the micro nozzle unit fuel inlets 412 and is externally supplied with fuel through the combustion chamber outer casing 6 via a fuel manifold interface 402. The micro nozzle assembly 4 works as follows: fuel enters the fuel manifold 401 through the fuel manifold interface 402, enters each micro nozzle unit 430 through the fuel inlet 412 of the micro nozzle unit 430, uniformly enters the space formed by the micro nozzle group shell 411 and the front cover 414 and the rear cover 415 of the micro nozzle group through the fuel uniformly distributor 413, then enters the annular space formed by the micro nozzle cartridge receiver 422 and the micro nozzle center body 423 through the fuel injection holes 421 in the micro nozzle 420, and is mixed with air from the diffuser 1 to form a combustible mixture, and combustion is performed downstream of the micro nozzle 420.
The flame tube 5 of the present invention is mainly composed of two concentric rings, and is shown in fig. 1 and 10 in detail. The front end of the flame tube 5 is connected with the inner and outer arc surfaces of the micro nozzle housing 411 in the micro nozzle assembly 4, the outer wall surface of the flame tube 5 is fixed on the combustion chamber outer casing 6 through pins, and the rear end is lapped on the turbine inlet section of the gas turbine. The wall surface of the flame tube 5 can adopt a cooling mode of film cooling, rib cooling, divergent cooling and the like and a combined cooling mode.
The front-end fuel injection assembly 2 of the present invention mainly comprises a front-end fuel injection pipe, a connector pipe, a mounting seat, etc., and is shown in fig. 1 in detail. The front fuel injection pipe is an annular circular pipe with fuel injection holes, is fixed on the wall surface of the casing behind the diffuser 1 through a connector pipe, and forms an included angle of 60-120 degrees with the air flow direction discharged by the diffuser 1, preferably has a value of 90 degrees, so that the mixing of fuel and air is facilitated.
The low-emission combustor disclosed by the invention is mainly applied to a gas turbine, and is particularly suitable for a aeroderivative gas turbine, but is not limited to the aeroderivative gas turbine. It is to be noted that the low emission combustor and the related fuel injection technology of the present invention, including the accompanying drawings, are described by way of example only in the specific form of an annular combustor, which is not meant to represent that the present invention is applicable only to annular combustors, and is easily generalized to other forms of gas turbine combustors such as split-tube, annular-tube, single-tube, etc. in light of the present invention. Meanwhile, the technology disclosed by the invention can be also used for equipment for burning gas fuel such as a gas boiler, drying and heating and the like through reasonable expansion and adaptive transformation.
The preferred combination of the fuel injection modes of the main nozzle, the micro nozzle and the like according to the invention is described in detail above, and different combination schemes can be adopted in specific implementation according to different application occasions and working conditions. The low emission combustor of the present invention includes a combination of four fuel injection modes including pilot fuel injection, main premixed fuel injection, diffusion fuel injection and micro premixed fuel injection, but it is not necessary to include these four fuel injection modes simultaneously in application. For example, a low emission combustor containing only the main nozzle assembly 3 and the forward fuel injection assembly 2, and no micro-nozzle assembly 4; or may be a low emission combustion chamber containing only the micro-nozzle assembly 4 and no other fuel injection means. The method can be flexibly combined according to application occasions and working conditions.
Example 1
In this embodiment, a split-tube type combustion chamber is taken as an example, and its application to this type combustion chamber is briefly described. The basic structure of the branched pipe-shaped combustion chamber is cylindrical, and the flame tube and the combustion chamber casing are both cylindrical. In the extreme case of an annular combustion chamber with an inner ring radius reduced to zero, the annular combustion chamber is similar to the basic structure of a can-type combustion chamber. Fig. 11 shows a specific structure that may be employed in a split-tube combustor with a combination of primary nozzles 320 and mini-nozzles 420. In fig. 11, a main nozzle 320 is centrally disposed, and a plurality of micro nozzles 420 are disposed around the main nozzle 320. FIG. 11 shows a specific arrangement of a nozzle at the head of a branched tubular combustion chamber, and other parts of the combustion chamber have similar structures to those of a traditional branched tubular combustion chamber, and also adopt structures such as a cylindrical flame tube and a transition section. The arrangement shown in FIG. 11 can make full use of the combustion chamber headspace, increasing the air ratio for premixed combustion, thereby reducing the equivalence ratio of the fuel in the nozzle, and more particularly, reducing NO in the combustion products X And (5) discharging. Meanwhile, the structure of the miniature nozzle is also beneficial to shortening the flame length, so that a shorter flame tube can be adopted, and the structure of the combustion equipment is more compact.
The foregoing description of the embodiments has been provided for the purpose of illustrating the general principles of the invention, and is not meant to limit the invention thereto, but to limit the invention thereto, and any modifications, equivalents, improvements and equivalents thereof may be made without departing from the spirit and principles of the invention.
Claims (20)
1. The combustion chamber with the main nozzle assembly and the micro nozzle assembly comprises a diffuser, the main nozzle assembly, the micro nozzle assembly, a flame tube and a combustion chamber casing, wherein the diffuser is arranged at the end part of the combustion chamber casing and is used for diffusing high-temperature and high-pressure air entering the combustion chamber in a speed reducing manner; the flame tube is arranged in the combustion chamber casing, and a part of air enters the flame tube through the cooling holes on the surface of the flame tube wall to cool the high-temperature part of the flame tube; the method is characterized in that:
the front end of the flame tube is provided with the main nozzle assembly and the micro nozzle assembly, and most of air entering through the diffuser is mixed with injected fuel through air channels of the main nozzle assembly and the micro nozzle assembly and then burnt in the flame tube;
the micro nozzle assembly comprises a fuel main pipe and N micro nozzle units, wherein N is a natural number, and the fan-shaped included angle beta of the micro nozzle units and the number N of the micro nozzle units meet the condition that Nxbeta=360; the micro nozzle unit comprises a plurality of micro nozzles, wherein the outer diameter of each micro nozzle is 3-15 mm, and the center distance between adjacent micro nozzles is 1.1-2 times of the outer diameter of each micro nozzle;
the miniature nozzle unit comprises a plurality of matching rings, the number of the matching rings is equal to that of main nozzles of the main nozzle assembly, and the main nozzles of the main nozzle assembly are assembled in the matching rings; and
the micro nozzle unit comprises a fuel uniformly-distributing device, wherein the fuel uniformly-distributing device is used for enabling fuel to uniformly enter the micro nozzle;
the main nozzle assembly comprises a double-channel nozzle rod, a fuel distributor and a main nozzle, wherein the main nozzle comprises a fuel injection blade, a swirl blade, a central blunt body front end, a central blunt body, a fuel separation plate and a nozzle casing;
the main premixed fuel enters one channel in the fuel distributor through one fuel channel in the double-channel nozzle rod, passes through an opening corresponding to the installation position of the fuel injection blade of the nozzle casing and enters the channel in the fuel injection blade, is injected into air from the diffuser through a fuel injection hole on the fuel injection blade, and is mixed with the air to form combustible mixed gas;
under the condition of ignition or low working condition of the combustion chamber, the diffusion fuel enters another channel in the fuel distributor through another fuel channel in the double-channel nozzle rod, passes through an opening of the nozzle casing corresponding to the installation position of the swirl vane, enters the annular channel in the central blunt body, is sprayed out from the fuel injection hole on the end face of the central blunt body, and is mixed with air after being rotationally guided by the swirl vane for combustion.
2. The combustor of claim 1, further comprising a pilot fuel injection assembly positioned between said diffuser and said main nozzle assembly, said pilot fuel injection assembly including a pilot fuel injection tube for injecting pilot fuel into the high velocity air stream after said diffuser for rapid mixing with air for combustion oscillations suppression.
3. The combustor of claim 2, wherein the fuel injection direction of the forward fuel injection assembly is at an angle of 60 ° to 120 ° to the direction of airflow exiting the diffuser;
the front fuel injection pipe is an annular circular pipe with fuel injection holes and is fixed on the wall surface of the casing behind the diffuser through a connector pipe.
4. The combustor according to claim 1, wherein structural parameters of the main nozzle assembly are:
K/H=1.5-2.5, wherein K is the inner diameter of the nozzle casing, and H is the outer diameter of the central blunt body;
l/k=0.3 to 0.8, where L is the distance between the end face of the central blunt body and the end face of the nozzle casing;
the included angle between the swirl vane and the central line of the central blunt body is 20-60 degrees;
the included angle between the fuel injection hole and the central line of the central blunt body is 10-60 degrees;
each two-channel nozzle bar is connected to at least one main nozzle and a corresponding fuel distributor.
5. A combustor according to claim 3, wherein the direction of fuel injection of the front fuel injection assembly is at an angle of 90 ° to the direction of airflow exiting the diffuser.
6. The combustion chamber of claim 4, wherein K/H = 2.
7. The combustor according to claim 4, wherein L/K = 0.5.
8. The combustor according to claim 4, wherein the swirl vanes are at an angle of 35 ° to the central bluff body centerline.
9. The combustion chamber of claim 4 wherein the fuel injection hole is angled at a preferred value of 45 degrees from the center blunt centerline.
10. The combustor of claim 1, wherein the micro-nozzle comprises a center body, micro-swirl vanes disposed around the center body, and a micro-nozzle case surrounding the micro-swirl vanes, the micro-nozzle case containing 1-8 micro-fuel injection holes.
11. The combustor according to claim 10, wherein the forward end of the centerbody is of a streamlined configuration.
12. The combustor of claim 10, wherein the number of micro-swirl vanes in the micro-nozzle is 2-12.
13. The combustion chamber of claim 10, wherein the ratio of the outer diameter of the centerbody to the inner diameter of the mini-nozzle casing is 0.2-0.6.
14. The combustor of claim 13, wherein the ratio of the outer diameter of the centerbody to the inner diameter of the mini-nozzle casing is 0.5.
15. The combustion chamber of claim 10, wherein the micro-nozzle is secured between a front cover and a rear cover of the micro-nozzle unit, and fuel injection holes contained in the micro-nozzle cartridge in the micro-nozzle are contained in a space formed by the front cover, the rear cover, and the housing of the micro-nozzle assembly.
16. The combustor according to claim 1, wherein the liner is comprised of two concentric rings; the front end of the flame tube is connected with the inner arc surface and the outer arc surface of the micro nozzle shell in the micro nozzle assembly; the outer wall surface of the flame tube is fixed on the combustion chamber outer casing, and the rear end of the flame tube is lapped on the turbine inlet section of the gas turbine.
17. The combustor of claim 16, wherein cooling of the liner employs one or a combination of film cooling, rib cooling, and divergent cooling.
18. The combustor of claim 1, wherein the fuel injection pattern of the combustor comprises at least one of a pilot fuel injection, a main premixed fuel injection, a diffusion fuel injection, and a micro premixed fuel injection.
19. The combustor according to claim 1, wherein the combustor is an annular, split-tube, can-annular or single-tube combustor.
20. Gas turbine, aeroengine and boiler employing a combustion chamber according to any of claims 1 to 19.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611163961.XA CN106524223B (en) | 2016-12-15 | 2016-12-15 | Combustion chamber with main nozzle assembly and mini-nozzle assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611163961.XA CN106524223B (en) | 2016-12-15 | 2016-12-15 | Combustion chamber with main nozzle assembly and mini-nozzle assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106524223A CN106524223A (en) | 2017-03-22 |
| CN106524223B true CN106524223B (en) | 2023-06-02 |
Family
ID=58340022
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611163961.XA Active CN106524223B (en) | 2016-12-15 | 2016-12-15 | Combustion chamber with main nozzle assembly and mini-nozzle assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106524223B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107975822B (en) * | 2017-12-19 | 2023-03-14 | 中国科学院工程热物理研究所 | Combustion chamber of gas turbine and gas turbine using combustion chamber |
| CN110953603B (en) * | 2019-12-05 | 2021-08-03 | 中国航发四川燃气涡轮研究院 | Multi-oil-path fuel oil spraying device suitable for radial grading main combustion chamber |
| CN111023152B (en) * | 2019-12-18 | 2021-03-09 | 西安航天动力研究所 | Rectification and injection integrated device and ramjet engine using same |
| DE102020128661A1 (en) | 2020-10-30 | 2022-05-05 | Rolls-Royce Deutschland Ltd & Co Kg | Nozzle for a combustion chamber of an engine with at least two nozzle heads |
| CN113722833B (en) * | 2021-09-09 | 2023-06-06 | 湖南工业大学 | Turbofan engine residual service life prediction method based on double-channel long-short-term memory network |
| CN114294680B (en) * | 2021-12-29 | 2023-07-04 | 哈尔滨工业大学 | Micro-premixing combustion chamber of central grading gas turbine |
| CN115435338B (en) * | 2022-11-09 | 2023-01-03 | 中国空气动力研究与发展中心超高速空气动力研究所 | Large-flow combustion heating injector adopting mixing nozzle |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2667047A1 (en) * | 2006-10-20 | 2008-04-24 | Ihi Corporation | Gas turbine combustor |
| CN101650038A (en) * | 2009-09-02 | 2010-02-17 | 北京航空航天大学 | Integrated diffusion oriented combustion chamber |
| CN101929678A (en) * | 2009-06-18 | 2010-12-29 | 通用电气公司 | The many fuel circuits that are used for pre-mix nozzle synthesis gas/NG DLN |
| CN102901127A (en) * | 2012-09-11 | 2013-01-30 | 北京航空航天大学 | Premixing pre-evaporation low-pollution combustion chamber for main-combustion-stage double-layer pre-film three-cyclone |
| CN102927592A (en) * | 2011-08-08 | 2013-02-13 | 通用电气公司 | Turbomachine combustor assembly |
| CN103196155A (en) * | 2012-01-04 | 2013-07-10 | 通用电气公司 | System comprising fuel nozzles for injecting fuel in a gas turbine combustor |
| CN103225823A (en) * | 2012-01-26 | 2013-07-31 | 通用电气公司 | Bundled multi-tube nozzle assembly, and method for reducing emissions in turbo machine |
| CN103277816A (en) * | 2013-05-10 | 2013-09-04 | 南京航空航天大学 | Lean oil pre-mixing pre-evaporation low-emission standing vortex combustion chamber |
| CN104566471A (en) * | 2014-12-30 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Spray nozzle and gas turbine with same |
| CN206361714U (en) * | 2016-12-15 | 2017-07-28 | 中国科学院工程热物理研究所 | Combustion chamber and gas turbine and boiler with main burner and micro nozzle component |
-
2016
- 2016-12-15 CN CN201611163961.XA patent/CN106524223B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2667047A1 (en) * | 2006-10-20 | 2008-04-24 | Ihi Corporation | Gas turbine combustor |
| CN101929678A (en) * | 2009-06-18 | 2010-12-29 | 通用电气公司 | The many fuel circuits that are used for pre-mix nozzle synthesis gas/NG DLN |
| CN101650038A (en) * | 2009-09-02 | 2010-02-17 | 北京航空航天大学 | Integrated diffusion oriented combustion chamber |
| CN102927592A (en) * | 2011-08-08 | 2013-02-13 | 通用电气公司 | Turbomachine combustor assembly |
| CN103196155A (en) * | 2012-01-04 | 2013-07-10 | 通用电气公司 | System comprising fuel nozzles for injecting fuel in a gas turbine combustor |
| CN103225823A (en) * | 2012-01-26 | 2013-07-31 | 通用电气公司 | Bundled multi-tube nozzle assembly, and method for reducing emissions in turbo machine |
| CN102901127A (en) * | 2012-09-11 | 2013-01-30 | 北京航空航天大学 | Premixing pre-evaporation low-pollution combustion chamber for main-combustion-stage double-layer pre-film three-cyclone |
| CN103277816A (en) * | 2013-05-10 | 2013-09-04 | 南京航空航天大学 | Lean oil pre-mixing pre-evaporation low-emission standing vortex combustion chamber |
| CN104566471A (en) * | 2014-12-30 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Spray nozzle and gas turbine with same |
| CN206361714U (en) * | 2016-12-15 | 2017-07-28 | 中国科学院工程热物理研究所 | Combustion chamber and gas turbine and boiler with main burner and micro nozzle component |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106524223A (en) | 2017-03-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106524223B (en) | Combustion chamber with main nozzle assembly and mini-nozzle assembly | |
| US7762073B2 (en) | Pilot mixer for mixer assembly of a gas turbine engine combustor having a primary fuel injector and a plurality of secondary fuel injection ports | |
| US5794449A (en) | Dry low emission combustor for gas turbine engines | |
| US7878000B2 (en) | Pilot fuel injector for mixer assembly of a high pressure gas turbine engine | |
| CN102748776B (en) | Apparatus and method for combusting fuel within a gas turbine engine | |
| CN102175043B (en) | Gas turbine engine combustor can with trapped vortex cavity | |
| US10465909B2 (en) | Mini mixing fuel nozzle assembly with mixing sleeve | |
| EP2481982B2 (en) | Mixer assembly for a gas turbine engine | |
| CN111316041B (en) | Gas turbine combustor assembly with trapped vortex feature | |
| US3931707A (en) | Augmentor flameholding apparatus | |
| CN111578311B (en) | Fuel nozzle assembly | |
| JP4997018B2 (en) | Pilot mixer for a gas turbine engine combustor mixer assembly having a primary fuel injector and a plurality of secondary fuel injection ports | |
| US20070028595A1 (en) | High pressure gas turbine engine having reduced emissions | |
| CN103032900A (en) | Triple annular counter rotating swirler | |
| CN113405119B (en) | Vortex-flow trapped-vortex partition combustion chamber | |
| CN108954388A (en) | A kind of multiple spot unit directly sprays fractional combustion room | |
| KR20140090141A (en) | Tangential annular combustor with premixed fuel and air for use on gas turbine engines | |
| CN115127123A (en) | Radial staged combustor, gas turbine power generation system and combustion regulation method | |
| CN116518417A (en) | Burner with fuel injector | |
| GB2451517A (en) | Pilot mixer for mixer assembly of a gas turbine engine combustor having a primary fuel injector and a plurality of secondary fuel injection ports | |
| KR102429643B1 (en) | System and method for improving combustion stability of gas turbine | |
| CN115597088B (en) | Combustion chamber structure and combustion regulation and control method | |
| CN113606040B (en) | Gas turbine power generation device adopting full-premixing low-nitrogen combustion mode | |
| KR102322598B1 (en) | Nozzle assembly for combustor and gas turbine combustor including the same | |
| KR102322596B1 (en) | Nozzle assembly for combustor and gas turbine combustor including the same |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20180621 Address after: 014070 Baotou, the Inner Mongolia Autonomous Region, Shiguai, Shiguai, Kwai Chuang New District, Shiguai science and technology building 313 room Applicant after: Inner Mongolia Zhongke Park stone gas turbine Co.,Ltd. Address before: 100190 North Fourth Ring Road, Haidian District, Beijing, 11 Applicant before: Institute of Engineering Thermophysics, Chinese Academy of Sciences |
|
| TA01 | Transfer of patent application right | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |