CN111649354B

CN111649354B - Three-cyclone classification cyclone and combustion chamber thereof

Info

Publication number: CN111649354B
Application number: CN202010542041.9A
Authority: CN
Inventors: 肖建昆; 李明玉
Original assignee: Jiangsu University of Science and Technology
Current assignee: Jiangsu University of Science and Technology
Priority date: 2020-06-15
Filing date: 2020-06-15
Publication date: 2022-03-29
Anticipated expiration: 2040-06-15
Also published as: CN111649354A

Abstract

The invention discloses a three-swirl staged swirler and its combustion chamber, wherein the swirler comprises an axial connecting piece and a radial connecting piece, the center of the axial connecting piece is provided with an axial through hole, and the The radial connector includes a first venturi and a second venturi that are coaxially and spaced apart, and a plurality of sets of annular arrays are fixedly connected in the annular space between the first venturi and the second venturi. The two sets of blades are fixedly connected with the first venturi and the second venturi, and the annular space is evenly divided into a plurality of relatively independent subspaces. Through the special structural design and arrangement of the swirler, the invention can not only achieve the goal of reducing pollutant emissions in the low-pollution combustion chamber, but also simplify the main combustion stage fuel supply system of the combustion chamber and reduce the main combustion stage fuel nozzles. Possibility of coking.

Description

Three-cyclone classification cyclone and combustion chamber thereof

Technical Field

The invention belongs to the technical field of combustion chambers, and particularly relates to a three-cyclone classification cyclone and a combustion chamber thereof.

Background

With the increasing concern of people on the environment and health, people pay more attention to various pollution sources which are harmful to the health of themselves and damage the environment and strictly control the pollution sources. Although aircraft engines and industrial gas turbines account for a small percentage of total combustion pollutant emissions, high concentrations of pollutant emissions accumulate due to their local characteristics, such as near airports and at the sites where industrial gas turbines are used. In the air, the pollutant emissions produced by various types of aircraft are the only source of high-altitude atmospheric pollutants. As a result, emissions from gas turbines, including aircraft engines and various industrial gas turbines, are increasingly more severely limited.

The standard for the emission of pollution of civil aviation gas turbines is promulgated by the international civil aviation organization. The current environmental protection activities of the international civil aviation organization are organized by the aviation environmental protection committee and currently the CAEP6 is performed, especially with increasingly stringent emission requirements for NOx.

For industrial gas turbines and marine gas turbines, due to different laws and regulations in various countries, no unified standard exists at present, and the unified standard is established according to the requirements of the countries and the regions on environmental protection. Worldwide, southern california and japan require legislation to limit NOx emissions to 9ppmv, the so-called single digit emission, due to strong public awareness of environmental protection. The emission standards in europe are generally similar to those of the united states environmental protection agency.

In order to meet the ICAO cae standards, research into low-pollution combustion technology has been conducted by various large airlines and research institutes. The GE company develops a TAPS low-pollution combustor for a GEnx engine, the Puhui company uses an RQL mode to reduce pollutant emission and develops TALON X, and the Roro company uses an LPP combustion organization mode to reduce the NOx pollution emission index in an ICAO CAEP2 standard by more than 70%. The Roro company also develops another low-pollution combustor, ANTLE, which applies LDM low-pollution combustion mode, and the experimental result shows that the NOx pollution emission is 50% lower than the current ICAO standard.

In the field of industrial gas turbines, each large gas turbine company has developed different types of low pollution combustors. A RB211-DLE industrial low-pollution combustion chamber of Roro company adopts a two-stage premixing combustion mode, the head part is a two-stage swirler, and a staged fuel nozzle is used for controlling the flame temperature in a flame tube. The emission of NOx pollutants is less than 25ppm, the emission of CO pollutants is less than 50ppm, and the fuel oil is gas-phase fuel. A TRENT industrial low-pollution combustion chamber of Roro company adopts a three-stage premixing mode, the head part is a two-stage swirler, and a graded fuel nozzle is used for controlling the flame temperature in a flame tube. The emission of NOx pollutants is less than 25ppm, the emission of CO pollutants is less than 5ppm, and the fuel oil is gas-phase fuel. The LM2500/6000 industrial low-pollution combustor of GE company has 75 double swirlers arranged in the annular combustor, and the two-stage swirlers are arranged in opposite rotating directions and three rows in radial directions. The gaseous fuel test results showed NOx pollutant emissions of less than 25ppm and CO pollutant emissions of 10 ppm.

Although the aero-engine or the ground gas turbine solves the emission requirements of the low-pollution gas turbine to different degrees, the structure and the oil supply system are complex, the weight is too high, and the three-cyclone classification cyclone and the combustion chamber thereof are provided for overcoming the defects.

Disclosure of Invention

The purpose of the invention is as follows: the invention aims to provide a three-cyclone classification swirler and a combustion chamber thereof, and the three-cyclone classification swirler not only can achieve the aim of reducing pollutant emission of a low-pollution combustion chamber, but also simplifies a main combustion stage oil supply system of a three-stage cyclone combustion chamber, reduces the possibility of coking of a main combustion stage fuel nozzle, and solves the problems of overhigh weight caused by the complexity of the structure and the oil supply system of the conventional engine through the special structural design and arrangement mode of the swirler.

The technical scheme is as follows: the invention relates to a three-cyclone grading cyclone which comprises an axial connecting piece and a radial connecting piece, wherein an axial through hole is formed in the center of the axial connecting piece, the radial connecting piece comprises a first venturi and a second venturi which are coaxial and arranged at intervals, a plurality of groups of blades arranged in an annular array are fixedly connected in an annular space between the first venturi and the second venturi, and two ends of the plurality of groups of blades are fixedly connected with the first venturi and the second venturi and uniformly divide the annular space into a plurality of relatively independent subspaces;

the axial connecting piece and the first venturi tube are coaxially arranged and fixedly connected, an axial through hole of the axial connecting piece is communicated with a center hole of the first venturi tube, multiple groups of first axial oblique cutting holes are arranged on the periphery of the axial through hole of the axial connecting piece in an annular array mode, the first axial oblique cutting holes are communicated with the center hole of the first venturi tube, multiple groups of second axial oblique cutting holes are arranged on the periphery of the end face of the axial connecting piece in an annular array mode, multiple groups of third axial oblique cutting holes are arranged on the periphery of the end face of the first venturi tube close to the axial connecting piece in an annular array mode, the third axial oblique cutting holes are in one-to-one correspondence with the second axial oblique cutting holes and are communicated with the second axial oblique cutting holes, and the other ends of the multiple groups of the third axial oblique cutting holes are in one-to-one correspondence with the multiple subspaces and are communicated with the subspaces.

Further, the diameter of the axial through hole of the axial connecting piece is smaller than that of the central hole of the first venturi tube, and the diameter of the central hole of the first venturi tube is smaller than that of the central hole of the second venturi tube.

Furthermore, the first axial oblique cutting hole is circular, and the airflow in the first axial oblique cutting hole flows to the center along the radial direction of the cyclone in the radial direction and is communicated with the airflow in the center hole of the first venturi. The first axially chamfered holes have an angle of between 30 and 60 degrees and a number of between 6 and 9.

Furthermore, the second axial oblique cutting hole is circular, and the airflow in the second axial oblique cutting hole flows along the radial outer edge of the cyclone in the radial direction and is communicated with the airflow in the third axial oblique cutting hole. The second axial chamfer holes are between 30 and 60 degrees in number of 6 to 9.

Further, the first axial oblique cutting holes and the second axial oblique cutting holes are arranged in a crossed mode.

A combustion chamber provided with the three-cyclone stage cyclone as in any one of the above claims, comprising a flame tube head, wherein the flame tube head consists of a pre-combustion stage and a main combustion stage, the pre-combustion stage comprises a pre-combustion stage centrifugal nozzle, and an outlet of the pre-combustion stage centrifugal nozzle is flush with an outlet of an axial connecting piece; the main combustion stage comprises a main combustion stage direct-injection nozzle, primary atomized fuel oil sprayed by the main combustion stage direct-injection nozzle is subjected to shearing secondary atomization with air entering an evaporation pipe, the primary atomized fuel oil is further subjected to evaporation mixing in the evaporation pipe through a second axial oblique-cut hole and a third axial oblique-cut hole after the primary atomized fuel oil is evaporated and mixed in the evaporation pipe, finally the secondary atomized fuel oil is subjected to secondary mixing with air passing through relatively independent subspaces, and the mixture reaches a required equivalence ratio and enters a flame tube through an annular space outlet between a first venturi tube and a second venturi tube.

Has the advantages that: compared with the prior art, the invention has the following advantages:

(1) the three-cyclone classification swirler of the invention integrally designs the pre-combustion level inclined-cut hole type swirler, the main combustion level inclined-cut hole type swirler and the main combustion level radial swirler, and due to the special design, the pre-mixing and pre-evaporation effects of main fuel oil are realized, and the pre-combustion level centrifugal nozzle and the main combustion level direct injection nozzle can be prevented from being coked too early due to the air cooling effect of the evaporation pipe;

(2) the fuel oil system of the combustion chamber is simpler, the head of the combustion chamber is more compact, the weight of the combustion chamber is greatly reduced, and high-efficiency low-emission combustion under a wider working condition can be realized.

Drawings

FIG. 1 is a schematic view of a three-cyclone stage cyclone of the present invention;

FIG. 2 is another angle structure diagram of the three cyclone stage cyclone of the present invention;

FIG. 3 is a schematic view of an axial connector configuration;

FIG. 4 is a front and rear view of the axial connector; (FIG. a shows a front view of the axial connector, and FIG. b shows a rear view of the axial connector)

FIG. 5 is a schematic view of a radial connector configuration;

FIG. 6 is a front view of a radial connector;

FIG. 7 is a schematic view of the combustion chamber of the present invention;

fig. 8 is an enlarged view of fig. 7 at a.

Detailed Description

The invention is further described below with reference to the following figures and examples:

as shown in fig. 1 and fig. 2, the three-cyclone stage cyclone of the present invention integrates the pre-combustion stage inclined-cut hole type cyclone, the main combustion stage inclined-cut hole type cyclone and the main combustion stage radial cyclone, the axial connecting piece comprises an axial connecting piece 1 and a radial connecting piece 2, wherein an axial through hole 11 is formed in the center of the axial connecting piece 1, the radial connecting piece 2 comprises a first venturi 21 and a second venturi 22 which are coaxial and arranged at intervals, a plurality of groups of blades 23 arranged in an annular array are fixedly connected in an annular space between the first venturi 21 and the second venturi 22, the installation angle of the blades 23 is between 30 and 45 degrees, the number of the blades 23 is 9 to 16, in the embodiment, the installation angle of the blades 23 is 30 degrees, the number of the blades 23 is 8, two ends of 8 groups of blades 23 are fixedly connected with the first venturi 21 and the second venturi 22, and the annular space is uniformly divided into 8 relatively independent subspaces 24;

as shown in fig. 3 to 6, the axial connection member 1 and the first venturi tube 21 are coaxially and fixedly connected, the axial through hole 11 of the axial connection member 1 is communicated with the central hole 211 of the first venturi tube 21, the diameter of the axial through hole 11 of the axial connection member 1 is smaller than that of the central hole 211 of the first venturi tube 21, the diameter of the central hole 211 of the first venturi tube 21 is smaller than that of the central hole 221 of the second venturi tube 22, 8 groups of first axial chamfered holes 12 are arranged in an annular array on the peripheral side of the axial through hole 11 of the axial connection member 1, 8 groups of first axial chamfered holes 12 are communicated with the central hole 211 of the first venturi tube 21, the first axial chamfered holes 12 are circular in shape, the angle of the first axial chamfered holes 12 is 30 degrees, and the air flow in the first axial chamfered holes 12 flows along the radial direction of the swirler to the center in the radial direction and is communicated with the air flow in the central hole 211 of the first venturi tube 21;

the periphery of the end face of the axial connecting piece 1 is provided with 8 groups of second axial oblique cutting holes 13 in an annular array, the first axial oblique cutting holes 12 and the second axial oblique cutting holes 13 are arranged in a crossed mode, namely 1 group of first axial oblique cutting holes 12 are matched with each other between every 2 groups of second axial

oblique cutting holes

13, and 1 group of second axial oblique cutting holes 13 are matched with each other in every 2 groups of first axial oblique cutting holes 12; the second axial oblique cutting holes 13 are circular, the angle of the second axial oblique cutting holes 13 is 30 degrees, and the airflow in the second axial oblique cutting holes 13 flows along the radial outer edge of the cyclone in the radial direction and is communicated with the airflow in the third axial oblique cutting holes 25; the periphery of the end face of the first venturi 21 close to the axial connecting piece 1 is provided with 8 groups of third axial oblique cutting holes 25 in an annular array, the third axial oblique cutting holes 25 are in one-to-one correspondence and communication with the second axial oblique cutting holes 13, and the other ends of the 8 groups of third axial oblique cutting holes 25 are in one-to-one correspondence and communication with the 8 subspaces 24;

as shown in fig. 7 and 8, the combustion chamber of the present invention has a three-swirl staged swirler, and further comprises a flame tube head 3, wherein the flame tube head 3 is composed of a pre-combustion stage 4 and a main combustion stage 5; the pre-combustion stage 4 and the main combustion stage 5 are assembled together in a central grading mode, the pre-combustion stage 4 is in the center, and the main combustion stage 5 is arranged on the outer side of the pre-combustion stage 4;

the pre-combustion stage 4 comprises a pre-combustion stage centrifugal nozzle 41, the pre-combustion stage centrifugal nozzle 41 is a pressure atomization nozzle, and the outlet of the pre-combustion stage centrifugal nozzle 41 is flush with the outlet of the axial connecting piece 1; the precombustion stage 4 adopts a single-oil-way centrifugal nozzle, and fuel oil is atomized by pressure to reach required concentration and size distribution, and specifically comprises the following steps: the fuel oil enters the pre-combustion level oil supply rod 43 through the pre-combustion level fuel oil pipe 42, then is supplied to the pre-combustion level centrifugal nozzle 41, is atomized and evaporated under pressure, is mixed with the air passing through the first axial oblique cutting hole 12 of the axial connecting piece 1 to reach the required equivalence ratio, and then enters the flame tube 6;

the main combustion stage 5 comprises a main combustion stage direct-injection nozzle 51, fuel oil of a main combustion stage fuel oil pipe 52 is sprayed out through an oil injection hole of the main combustion stage direct-injection nozzle 51, the fuel oil is sprayed to a main combustion stage venturi pipe 53 to be atomized for the first time, the fuel oil atomized for the first time and air in an evaporation pipe 54 are atomized for the second time under the action of shearing force of the air, the secondarily atomized main combustion stage fuel oil is further mixed with the air in the evaporation pipe 54, further evaporated and mixed through a second axial oblique-cutting hole 13 and a third axial oblique-cutting hole 25, and finally mixed with the air passing through a relatively independent subspace 24, and the mixed fuel oil enters the flame tube 6 through an annular space outlet between the first venturi pipe 21 and the second venturi pipe 22 to achieve the required equivalence ratio.

Because the temperature of the air entering the flame tube 6 is high, and the combustion chamber works, the temperature of the head part 3 of the flame tube is overhigh through the modes of heat conduction, heat convection, heat radiation and the like, and fuel oil is easy to coke in each oil pipe and nozzle, the head part of the combustion chamber can well solve the problem of coking of the fuel oil at key parts through special structural design, when the pre-combustion stage 4 supplies oil and the main combustion stage 5 does not supply oil, the air passing through the evaporation pipe 54 can cool the pre-combustion stage oil supply rod 43 and the pre-combustion stage centrifugal nozzle 41 to prevent the pre-combustion stage oil supply rod from coking; when the pre-combustion stage 4 is supplied with oil and the main combustion stage 5 is also supplied with oil, the air entering the evaporation pipe 54 is mixed with the main combustion stage fuel oil to cool the main combustion stage direct injection nozzle 51, the pre-combustion stage fuel supply rod 43 and the pre-combustion stage centrifugal nozzle 41;

the three-cyclone classification swirler of the invention integrally designs the pre-combustion level inclined-cut hole type swirler, the main combustion level inclined-cut hole type swirler and the main combustion level radial swirler, and due to the special design, the pre-mixing and pre-evaporation effects of the main fuel are realized, the weight of the flame tube head 3 is reduced, the disassembly and the assembly are convenient, and the maintainability of a combustion chamber is improved; meanwhile, due to the air cooling effect of the evaporation pipe 54, the precombustion stage centrifugal nozzle 41 and the main combustion stage direct-injection nozzle 51 can be prevented from coking prematurely; the fuel system of the combustion chamber is simpler, the head of the combustion chamber is more compact, and high-efficiency low-emission combustion under wider working conditions can be realized.

Claims

1. A three-cyclone grading cyclone is characterized in that: comprising an integrally formed axial connecting piece and a radial connecting piece, the center of the axial connecting piece is provided with an axial through hole, and the radial connecting piece is provided with an axial through hole. The component includes a first venturi and a second venturi that are coaxially and spaced apart, and a plurality of sets of blades arranged in an annular array are fixedly connected in the annular space between the first venturi and the second venturi , the two ends of the plurality of groups of the blades are fixedly connected with the first venturi and the second venturi, and the annular space is evenly divided into a plurality of relatively independent subspaces;

The axial connecting piece and the first venturi are coaxially arranged and integrally formed, and the axial through hole of the axial connecting piece communicates with the central hole of the first venturi, and the axial through hole of the axial connecting piece is on the peripheral side. A plurality of groups of first axial chamfered holes are arranged in an annular array, the first axial chamfered holes communicate with the central hole of the first venturi, and the peripheral side of the end face of the axial connecting piece is arranged in an annular array with A plurality of groups of second axially chamfered holes, a plurality of groups of third axial chamfered holes are arranged in an annular array on the peripheral side of the end face of the first venturi close to the axial connecting piece, and the third axially chamfered holes One-to-one correspondence and communication with the second axial chamfered holes, and the other ends of the plurality of groups of third axial chamfered holes correspond to and communicate with a plurality of subspaces one-to-one.

2 . A three-cyclone staged cyclone according to claim 1 , wherein the diameter of the axial through hole of the axial connecting piece is smaller than the diameter of the central hole of the first venturi, and the diameter of the first venturi is smaller than that of the first venturi. The central hole diameter of the venturi is smaller than the central hole diameter of the second venturi.

3 . The three-cyclone classification cyclone according to claim 1 , wherein the shape of the first axially chamfered hole is circular, and the airflow in the first axially chamfered hole is radially oriented. 4 . The direction flows toward the center along the radial direction of the cyclone, and communicates with the airflow in the central hole of the first venturi.

4. A three-cyclone classification cyclone according to claim 1, characterized in that: the shape of the second axially chamfered hole is circular, and the air flow in the second axially chamfered hole is in diameter The direction flows along the radially outer edge of the cyclone, and communicates with the airflow of the third axially chamfered hole.

5 . The three-cyclone classification cyclone according to claim 1 , wherein the first axially chamfered holes and the second axially chamfered holes are arranged in a cross. 6 .

6. A combustion chamber provided with the three-swirl staged swirler according to any one of claims 1 to 5, comprising a flame tube head, characterized in that: the flame tube head is composed of a pre-combustion stage and a main combustion stage. The pre-combustion stage includes a centrifugal nozzle of the pre-combustion stage, and the outlet of the centrifugal nozzle of the pre-combustion stage is flush with the outlet of the axial connecting piece; the main combustion stage includes a direct injection nozzle of the main combustion stage. The primary atomized fuel sprayed from the direct injection nozzle of the combustion stage is subjected to shearing and secondary atomization with the air entering the evaporating tube, and after being evaporated and blended in the evaporating tube, it passes through the second axial oblique cutting hole and the third axial oblique cutting hole. The cut hole is further evaporated and blended, and finally blended with the air passing through a relatively independent subspace, and the blending reaches the required equivalence ratio and enters through the annular space outlet between the first venturi and the second venturi in the flame tube.