CN115031259B - Combustion chamber of gas turbine and design method thereof - Google Patents
Combustion chamber of gas turbine and design method thereof Download PDFInfo
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- CN115031259B CN115031259B CN202210274928.3A CN202210274928A CN115031259B CN 115031259 B CN115031259 B CN 115031259B CN 202210274928 A CN202210274928 A CN 202210274928A CN 115031259 B CN115031259 B CN 115031259B
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- 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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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Abstract
A combustion chamber of a gas turbine and a design method thereof comprise a combustion chamber casing, an annular flame tube, a flame tube head, a nozzle assembly, a nozzle mounting seat and a design method thereof, wherein the flame tube head is uniformly distributed along the circumferential direction, and the nozzle assembly is correspondingly arranged and fixed on the combustion chamber casing through the nozzle mounting seat. Through the design of flame tube head and nozzle assembly, obtain stronger backward flow district, good fuel atomization evaporation and oil gas blending combustion, compare present gas turbine combustion chamber, hold hot strength high, can improve gas turbine work load, secondly straight hole and chute complex swirler have strengthened the gas blending when guaranteeing combustion stability, have effectively reduced the pollution emission. The method for designing the combustion chamber determines the total open area based on the jet flow speed of the flame tube, and excavates the combustion potential of the large air inflow of the head part on the basis of guaranteeing the cooling requirement of the combustion chamber.
Description
Technical Field
The invention relates to a combustion chamber of a ground gas turbine, in particular to a combustion chamber of a gas turbine and a design method thereof.
Background
In recent years, micro power systems have become research hotspots at home and abroad, and various countries in the world have invested a great deal of research in this respect, and micro gas turbines have the advantages of small volume, light weight, low cost and the like, and combustion chambers are important components of the micro gas turbines and are power sources of the gas turbines, and compared with conventional-scale combustion chambers, the micro gas turbines have the following characteristics: the length of the combustion chamber is short, the residence time of the fuel is short, atomization is difficult, and insufficient combustion is easy to cause; the volume of the combustion chamber is small, the volume of the main combustion area is small, and the combustion stability is adversely affected; the larger surface area to volume ratio increases the heat transfer loss and is easy to cause flameout of the combustion chamber. The existing miniature combustion chamber mainly adopts an annular direct-current combustion chamber structural form, and is structurally formed by inheriting a conventional combustion chamber, and mainly comprises a combustion chamber casing, a flame tube, a head assembly, a fuel nozzle, an ignition device and the like.
In the development of the combustion chamber for many years, the micro combustion chamber mostly adopts gas fuel such as natural gas and the like as a combustion medium thereof, and the use of the gas fuel well solves the problem of insufficient combustion and difficult atomization of the combustion chamber.
In combination, in order to improve the performance index of the gas turbine combustor outlet, to complete the conversion of the combustion medium from the gaseous fuel to the liquid fuel, it is necessary to adaptively improve the existing combustor structure.
Disclosure of Invention
The invention is based on the basic structure of the gas combustion chamber to the important part of the combustion organization, namely the combustion chamber head is improved and designed, the oil supply mode of the combustion chamber head of the existing gas turbine and the organization combustion technology are improved to meet the use requirement of fuel and avoid the problems of poor fuel atomization effect, insufficient residence time and the like, and meanwhile, the design method of the gas turbine combustion chamber is provided to solve the defects in the prior art, and the invention discloses a gas turbine combustion chamber and a design method thereof, the technical scheme is as follows:
be applied to flame tube of gas turbine combustion chamber, including flame tube body, flame tube head, characterized by: the flame tube body forms an annular combustion cavity between the flame tube outer ring and the flame tube inner ring, and a plurality of flame tube heads are uniformly distributed in the circumferential direction of the annular flame tube body; each flame tube head adopts a cyclone designed by a combination mode of straight holes and inclined grooves, wherein the straight holes are uniformly distributed in the middle of the head in a circular circumferential direction, and the inclined grooves are arranged on the outer circumference of the flame tube head.
The invention also discloses a combustion chamber of the gas turbine, which comprises a combustion chamber casing, a nozzle assembly and a flame tube, and is characterized in that: the flame tube head is correspondingly provided with a nozzle assembly, and the nozzle assembly is fixed on the combustion chamber casing through a nozzle mounting seat; the nozzle mounting seat completes axial positioning with the casing through the two support rings, and the relative positions of the nozzle head and the flame tube head are adjusted through the positions of the support rings.
The invention also discloses a gas turbine combustion chamber design method, which comprises the gas turbine combustion chamber and is characterized in that:
step 1: determining specific indexes of a combustion chamber according to the overall design requirement of the gas turbine: the inlet total pressure, the temperature, the air flow and the outlet temperature and the outlet total pressure parameters of the combustion chamber in the design state;
step 2: the combustion chamber is selected according to the parameters determined by the combustion chamber: a multi-head direct-current combustion chamber is adopted; in order to reduce the influence of the NOx in the combustion chamber on the environment, the air involved in combustion is mainly fed by the head of the flame tube; in order to ensure the service life of the flame tube, the annular flame tube is to adopt a high-efficiency multi-inclined-hole cooling mode;
step 3: determining design parameters of a combustion chamber casing and a flame tube;
step 4: determining the effective area of the flame tube opening of the combustion chamber according to inlet parameters and inlet and outlet pressures of the design state of the combustion chamber;
step 5: determining cooling parameters of the head of the flame tube;
step 6: determining cooling parameters of an outer ring of the flame tube;
step 7: determining cooling parameters of an inner ring of the flame tube;
step 8: determining parameters of the cyclone;
step 9, determining nozzle head parameters;
step 10: the combustion chamber ignition mode is determined.
The beneficial effects are that:
aviation kerosene is adopted as a combustion medium, so that the upper limit of the performance of the combustion chamber can be further improved, and meanwhile, the head of the combustion chamber is subjected to targeted improvement, so that the performance of the combustion chamber is stabilized; the invention carries out standardization design on the design flow of the combustion chamber of the miniature gas turbine by taking aviation kerosene as a combustion medium, designs a combustion chamber structure with stable performance according to the design flow, and can meet the design requirement; the nozzle assembly is designed in detail, so that the problem of installation and combustion chamber atomization caused by changing combustion media can be effectively solved.
Drawings
FIG. 1 is a schematic view of a circumferential distribution of a combustion chamber;
FIG. 2 is a general view of a combustion chamber structure;
FIG. 3 is a schematic view of a flame tube head design;
FIG. 4 is a schematic view of the nozzle assembly installation positioning;
FIG. 5 is a schematic view of a nozzle head and mounting base;
FIG. 6 is a schematic diagram of a liner head cooling design.
Wherein: 1 a nozzle assembly; 2, a flame tube; a 21 flame tube outer ring; 22 inner rings of flame tubes; 23 a flame tube head; 3, a combustion chamber; 11 nozzle heads; 12 a nozzle support ring; 13 a nozzle holder; 4, a combustion chamber casing; 5, igniting the nozzle; 231 straight holes; 232 chute.
Detailed Description
The present invention provides a gas turbine combustor, as shown in fig. 1 and 2, comprising a combustor casing 4, an annular flame tube 2, a nozzle assembly 1 and an ignition tip 5. More specifically, in the illustrated embodiment, the liner 2 includes a liner outer ring 21 and a liner inner ring 22, and an annular combustion chamber 3 is formed between the liner outer ring 21 and the liner inner ring 22, the annular combustion chamber 3 assuming a shape contracted in the axial direction by the restriction of the inner and outer rings; the nozzle assembly 1 is fixed on the combustion chamber casing 4 through a nozzle seat assembly, the head of the nozzle assembly enters the annular combustion chamber 3 through the head of the flame tube, and the distance of the head entering the annular combustion chamber can be adjusted through the support ring; the fuel is atomized by the nozzle assembly 1 and enters the annular combustion chamber 3 to be mixed with the air entering from the head and is ignited by the ignition electrode 5 in the main combustion area to perform combustion reaction.
Be applied to flame tube of gas turbine combustion chamber, including flame tube body, flame tube head, characterized by: the flame tube body forms an annular combustion cavity between the outer ring of the flame tube body and the inner ring of the flame tube body, and a plurality of flame tube heads are uniformly distributed in the circumferential direction of the annular flame tube body; each flame tube head adopts a combined mode of straight holes and inclined grooves, wherein the straight holes are uniformly distributed in the middle of the head in the circumferential direction, and the inclined grooves are arranged on the outer circumference of the flame tube head; in order to meet the structure and strength of a backflow area required by fuel oil combustion, the head part 23 of the flame tube adopts a combination mode of straight holes and inclined grooves, wherein the straight holes 231 are arranged in the middle of the head part and are uniformly distributed in the circumferential direction in a circular shape, the dividing circles are 32mm in diameter and 12 in number, each diameter is 4mm, and the air inlet ratio of the head part position of the flame tube is improved through the design of the straight holes of the head part; the chute sets up on the outside circumference of flame tube head 23, and the fluting quantity is 20, and the groove width is 2.7mm, and the groove depth is 3mm, and through optimizing the selection groove and central line contained angle is 55 degrees, under this kind of design, the air current is through the whirl groove with higher speed rotatory air current velocity gradient of flame tube head is big, and with center head shearing action between admitting air is strong, is favorable to the mixing effect of fuel, refer to fig. 3.
In this embodiment, the gas turbine combustor further includes a nozzle assembly 1, the nozzle assembly 1 is an important part of the combustor design, the gas-oil ratio of the head is controlled by matching with the flame tube head 23 so as to affect the combustion of fuel in the annular combustion chamber 3, and the oscillating combustion of the combustion is often related to the relative positions of the nozzle assembly 1 and the flame tube head 23, in this embodiment, the nozzle assembly 1 is axially positioned by two nozzle support rings 12, and then the relative positions of the nozzle assembly 1 and the head are adjustable.
As shown in fig. 4 and 5, the nozzle assembly 1 includes a nozzle head 11 and a nozzle holder 13 connected by screw threads. The nozzle head 11 is designed to adopt a direct-injection type atomizing nozzle for realizing the purpose of taking aviation kerosene as fuel, and small holes with the diameter of 0.7mm are arranged at an outlet according to the fuel flow and atomizing requirements, so that the spray is hollow cone-shaped and uniform; the internal channel of the nozzle seat 13 is in a straight circular tube shape, the total length of the nozzle seat 13 is set to 120.4mm in consideration of structural assembly limitation and the speed of fuel oil reduced as far as possible, the fuel oil is finally sprayed out through a nozzle, and the inlet of the nozzle seat is connected with a fuel oil main pipe.
The invention also discloses a combustion chamber of the gas turbine and a design method thereof, comprising the following steps:
step one: explicit overall demand: determining specific indexes of a combustion chamber according to the overall design requirement of the gas turbine: the inlet total pressure, the temperature, the air flow and the outlet temperature and the outlet total pressure parameters of the combustion chamber in the design state;
the gas turbine generally provides requirements, when the total inlet pressure of the combustion chamber at a design point is 431.341kpa, the temperature is 477.45K, the air flow rate is 3.136kg/s, the outlet temperature of the combustion chamber must reach 1203.0K, the total outlet pressure is not lower than 414.087kpa, and the fuel requirement is aviation kerosene.
Step two: the basic type of combustion chamber is determined.
Aviation kerosene is used as a high-quality fuel selected by a combustion chamber of a gas turbine, has the characteristics of high heat value, high efficiency and the like, and is mainly used for the combustion chamber in a combustion organization mode adopting diffusion combustion, and fig. 1 and 2 show a basic structure of the combustion chamber adopted in the embodiment, and a multi-head direct-current combustion chamber is adopted; in order to reduce the influence of the NOx in the combustion chamber on the environment, the air involved in combustion is mainly fed by the head of the flame tube; in order to ensure the service life of the flame tube, the annular flame tube is to adopt an efficient multi-inclined-hole cooling mode.
Step three: and (3) designing the overall scheme of the combustion chamber, and determining design parameters of a casing and a flame tube of the combustion chamber.
The outer contour diameter of the combustion chamber casing is 563mm, the inner casing diameter is 286mm, the flame tube does not provide enough cooling air flow in order to ensure stable flow velocity in two channels of the combustion chamber, the reference cross-sectional area of the flame tube is designed to be 51.8% of the reference cross-sectional area of the combustion chamber, the cross-sectional area of the flame tube is 95585mm < 2 >, the outer diameter of the flame tube is 490mm, the inner diameter is 344mm, the two flow areas of the outer ring are 799172, and the two flow areas of the inner ring are 322312.
The fuel flow is iterated by using CHEMKIN software, the requirement that the inlet temperature of a combustion chamber is 477.45K, the outlet temperature of the combustion chamber after 3.136kg/s of air and fuel are combusted reaches 1203K under the condition that the pressure is 431.341kPa is met, the design flow of aviation kerosene (C12H 23) is 63g/s, the design requirement is met, and the NOx emission is lower. Therefore, the design point oil-gas ratio of the combustion chamber of the embodiment is 0.02, and the main combustion area of the combustion chamber is lean combustion because the combustion chamber belongs to a ground micro gas turbine and is mainly biased to low pollution and high stability, so that the inlet end wall of the flame tube and the inner and outer rings of the flame tube are ensured to have enough cooling gas, and the rest air enters from the head of the flame tube.
Step four: total open area design
From the combustor inlet parameters, the inlet air density can be calculated:
wherein:
for the combustion chamber inlet pressure +.>
For the inlet air flow temperature of the combustion chamber, R is constant (generally, the value 287.15)
According to the inlet and outlet pressure of the combustion chamber, the recovery coefficient of the total pressure of the combustion chamber is 0.96, and the jet flow speed of the flame tube is:
wherein: ΔP is the total pressure change value of the air flow entering the flame tube
Effective area of the flame tube opening:
since the liner outlet is to be coupled to the turbine, the liner outlet radial dimension is determined by the overall, the liner axial length must meet the gas residence time, i.e., not less than 12ms, so the liner length is determined to be 150mm, the basic configuration of the inner liner outer ring is determined, as at 21 and 22 in fig. 2; according to the contour of the flame tube of the preliminary design, the end wall of the head of the flame tube needs to be cooled by about 68942.2mm2, the outer ring of the flame tube needs to be cooled by about 156891.1mm2, and the inner ring of the flame tube needs to be cooled by about 122804.9mm2.
Step five: determining the cooling parameters of the head of the flame tube:
head air cooled G c The cooling was carried out with straight holes according to a design of 0.5 kg/(s.m2.bar). According to formula (2-4), the end wall of the head of the flame tube at the design pointThe amount of cooling air in (a) was 0.149kg/s. At this time, the effective area of the head cooling holes is 451.1mm2, the flow coefficient of the holes is 0.8, the geometric area is 563.9mm2, the hole diameter is 2mm, 179.5 holes are needed for head cooling through calculation, and 180 holes are selected.
Wherein: gc is a design parameter, the value is 0.5 kg/(s.m2.bar), A is the open area of the end wall of the head of the flame tube
The end wall of the head is radially divided into 5 rows of holes, namely 60 holes in the 1 st row, 20 holes in the 2 nd row, 20 holes in the 3 rd row, 20 holes in the fourth row and 60 holes in the fifth row, wherein the distribution of the 60 holes in the fifth row is shown in fig. 6, and the total effective area of the holes is 452.4mm < 2 >.
Step six: design of cooling parameters of outer ring 21 of flame tube
G of the outer ring 21 of the flame tube c According to the design of 0.8 kg/(s.m2.bar), the other four rows adopt inclined holes with an included angle of 30 degrees with the wall surface except for a row of straight holes which are arranged to be vertical to the wall surface of the flame tube near the head of the flame tube.
According to the formula (2-4), the cooling air amount of the liner outer ring 21 at the design point is 0.541kg/s; at this time, the effective area of the cooling holes of the outer ring 21 of the flame tube is 1642.6mm2, the flow coefficient of the holes is 0.6, the geometric area is 2737.7mm2, the hole diameter of the holes is 2mm, 871.5 holes are needed through calculation, and 900 holes are selected; 180 holes in each row, arranged in 5 rows; the cooling hole openings of the outer ring 21 of the burner tube are shown in fig. 2. The total effective area of the openings was 2261.9mm2.
Step seven: design of cooling parameters of inner ring 22 of flame tube
G for cooling inner ring 22 of flame tube c According to the design of 0.8 kg/(s.m2.bar), the other four rows adopt inclined holes with an included angle of 30 degrees with the wall surface except for a row of straight holes which are arranged to be vertical to the wall surface of the flame tube near the head of the flame tube. According to the formula (2-4), the cooling air amount of the inner ring 22 of the flame tube is 0.379kg/s at the design point; at the moment, the effective area of a cooling opening of the inner ring 22 of the flame tube is 1149.9mm2, the flow coefficient of the taking opening is 0.6, the geometric area is 1916.6mm2, and the opening is formedThe aperture is 2mm, 610.1 openings are needed after calculation, and 600 openings are selected; 120 holes per row are arranged in 5 rows. The cooling hole openings of the inner liner 22 of the burner are shown in fig. 2-3. At this time, the total effective area of the openings is 1508.0mm2;
step eight: cyclone parameter design
The cyclone is the most important guarantee for stable combustion of the combustion chamber, and the head of the combustion chamber adopts a combination mode of straight holes and inclined grooves to stabilize flame in a central backflow area. The total open area of the flame tube is 9515mm2, the open area of the head cyclone is 9515-452.4-2261.9-1508 = 5292.7mm2, the number of heads is determined according to the length of the central line of the head of the flame tube and the height of the head, 22 heads can be arranged at most through calculation, the number of the heads of the flame tube is 20 according to the requirements and economy of flame cross-connection of each head in the flame tube, and the effective area of the open hole of the single head is 264.6mm2.
The flame tube head adopts a combination mode of straight holes and inclined grooves: setting the number of straight holes to be 12, wherein each diameter is 4mm, the included angle between the center of each hole and the central line is 30 degrees, the flow coefficient is 0.8, and the effective area is 120.6mm2; the number of the chute is 20, the width of the chute is 2.7mm, the depth of the chute is 3mm, the included angle between the chute and the central line is-55 degrees, the flow coefficient is 0.75, and the effective area is 145.8mm < 2 >. The burner head is shown in fig. 3.
According to the design, the equivalence ratio of the main combustion area of the combustor is about 0.52, the flow distribution of the flame tube is shown in the following table 1, the basic principle of the flow distribution is to meet the requirement of the equivalence ratio in the main combustion area of the combustor, provide enough cooling air for the wall surface of the flame tube and ensure the distribution of an outlet temperature field, so that the head air ratio is large for maintaining combustion, the contraction structure at the rear end of the combustor enables a high-temperature area to be close to an outer annular wall surface, and the cooling air of the outer annular ring is slightly higher than that of the inner annular ring, so that the wall surface of the flame tube is prevented from being ablated by high-temperature fuel gas to generate cracks or even fall blocks.
TABLE 1 flame tube flow distribution
| Sequence number | | Flow distribution | |
| 1 | Flame tube head | 55.8％ | |
| 2 | Head end wall cooling | 4.7％ | |
| 3 | Outer ring cooling of flame tube | 23.7％ | |
| 5 | Inner ring cooling of flame tube | 15.8％ | |
| Total amount of | 100％ |
Step nine: and (5) designing nozzle head parameters.
The pressure atomizing nozzle with a single oil way is adopted, the finished fuel nozzle can be directly selected according to the requirement, the design flow is 3g/s, the spray cone angle is between 110 and 130 degrees, and the SMD is not more than 12 microns.
Step ten: the ignition mode of the combustion chamber is determined.
The electric spark igniter is adopted, a matched system can be directly selected, and the electric spark igniter mainly comprises a high-voltage cable, an igniter and an electric nozzle, wherein the igniter stores energy 12J, the input voltage AC220V, the input power 2.2kw, the spark frequency 10sps and the output voltage 2500V.
The invention improves the prior art, changes the combustion reaction substances of the combustion chamber of the micro gas turbine, changes the combustion chamber of the micro gas turbine into the fuel combustion chamber, and improves the adaptability of the key part of the combustion chamber, namely the head part of the flame tube. Based on the technical requirements, the swirl intensity of the backflow area is increased by increasing the swirl groove angle of the head part of the flame tube, meanwhile, the strong shearing action between the rotary airflow and the central straight hole air inlet can promote atomization, evaporation and blending of fuel oil, and the basic principle, main characteristics and advantages of the invention are shown and described above by avoiding increasing the axial length of the combustion chamber to meet the residence time required by combustion. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made therein without departing from the spirit and scope of the invention, which is defined by the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (1)
1. A method of designing a gas turbine combustor, comprising a gas turbine combustor, the combustor being: the burner comprises a nozzle box, a component combustion chamber machine and a flame tube, wherein the head of the flame tube is correspondingly provided with a nozzle component which is fixed on the combustion chamber machine box through a nozzle seat; the nozzle seat completes axial positioning with the casing through two support rings, and the relative positions of the nozzle head and the flame tube head are adjusted through the positions of the support rings; the nozzle assembly comprises a nozzle head and a nozzle seat connected through threads; the nozzle head adopts a direct-injection type atomizing nozzle to realize that aviation kerosene is used as fuel, a small hole with the diameter of 0.7mm is arranged at an outlet according to the fuel flow and atomizing requirements, the spray is hollow cone-shaped, and the atomization is uniform; the internal channel of the nozzle seat is in a straight round tube shape, and the inlet of the nozzle seat is connected with the fuel oil main pipe; aviation kerosene is adopted as a combustion medium in the combustion chamber; the flame tube comprises a flame tube body and a flame tube head; the flame tube body forms an annular combustion cavity between the outer ring of the flame tube body and the inner ring of the flame tube body, and a plurality of flame tube heads are uniformly distributed on the circumference of the annular flame tube heads; each flame tube head adopts a combined mode of straight holes and inclined grooves, wherein the straight holes are uniformly distributed in the middle of the head in the circumferential direction, and the inclined grooves are arranged on the outer circumference of the flame tube head; the number of the flame tube heads is 20, each head adopts a structure of straight holes and inclined grooves, the number of the straight holes is 12, the diameter of the straight holes is 4mm, the straight holes are uniformly distributed along the circumference with the diameter of 32mm, the inclined grooves are uniformly distributed on the circumference of the flame tube head, the number of grooves is 20, the groove width is 2.7mm, and the groove depth is 3mm; the included angle between the chute and the central line is 55 degrees; the method is characterized in that:
step 1: determining specific indexes of a combustion chamber according to the overall design requirement of the gas turbine: the inlet total pressure, the temperature, the air flow and the outlet temperature and the outlet total pressure parameters of the combustion chamber in the design state;
step 2: the combustion chamber is selected according to the parameters determined by the combustion chamber: a multi-head direct-current combustion chamber is adopted; in order to reduce the influence of the NOx in the combustion chamber on the environment, the air involved in combustion is mainly fed by the head of the flame tube; in order to ensure the service life of the flame tube, the annular flame tube is to adopt a high-efficiency multi-inclined-hole cooling mode;
step 3: determining design parameters of a combustion chamber casing and a flame tube;
step 4: determining the effective area of the flame tube opening of the combustion chamber according to inlet parameters and inlet and outlet pressures of the design state of the combustion chamber;
step 5: determining the cooling parameters of the head of the flame tube:
the head air cooling adopts straight hole cooling, and then the relation between the opening of the end wall of the head of the flame tube and the head cooling air flow is as follows:
wherein: gc is a design parameter, the value of Gc is 0.5 kg/(s.m2.bar), and A is the open area of the end wall of the head of the flame tube;
determining the cooling air quantity and the head cooling open area of the end wall of the head of the flame tube at the design point through the method;
step 6: determining cooling parameters of an outer ring of the flame tube;
step 7: determining cooling parameters of an inner ring of the flame tube;
step 8: determining parameters of the cyclone;
step 9, determining nozzle head parameters;
step 10: determining a combustion chamber ignition mode;
wherein: the method for the effective area of the flame tube opening of the combustion chamber comprises the following steps: calculating the inlet air density according to the inlet parameters of the combustion chamber:
wherein:
for the combustion chamber inlet pressure +.>
R is a constant value 287.15 for the inlet airflow temperature of the combustion chamber; />
According to the inlet and outlet pressure of the combustion chamber, the recovery coefficient delta of the total pressure of the combustion chamber can be known, and the jet flow speed of the flame tube:
wherein: ΔP is the total pressure change value of the air flow entering the flame tube,
；
effective area of the flame tube opening:
，
wherein: q is the mass flow of the inlet airflow of the combustion chamber, A is the open area of the flame tube, and Cd is the open flow coefficient; the inner ring and the outer ring of the flame tube adopt an impact cooling mode; when the design point is reached, the cooling air quantity of the head part of the flame tube is 0.149kg/s, the cooling air quantity of the outer ring of the flame tube is 0.541kg/s, and the cooling air quantity of the inner ring of the flame tube is 0.379kg/s; the flow distribution of the combustion chamber is as follows, the gas quantity of the head part of the flame tube is 55.8 percent, the cooling rate of the end wall of the head part is 4.7 percent, the cooling rate of the outer ring of the flame tube is 23.7 percent, and the cooling rate of the inner ring of the flame tube is 15.8 percent; the head of the flame tube adopts a straight hole and chute combined rotational flow mode, the total open area is 5292.7mm2, the number of the selected heads is 20, and the effective open area of a single head is 264.6mm2.
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| US8438851B1 (en) * | 2012-01-03 | 2013-05-14 | General Electric Company | Combustor assembly for use in a turbine engine and methods of assembling same |
| US10317083B2 (en) * | 2014-10-03 | 2019-06-11 | Pratt & Whitney Canada Corp. | Fuel nozzle |
| CN107992655A (en) * | 2017-11-22 | 2018-05-04 | 北京动力机械研究所 | The quick Virtual Numerical Experiments method of deflector type combustion chamber aeroperformance |
| CN108716695A (en) * | 2018-04-02 | 2018-10-30 | 西北工业大学 | A kind of tiny engine combustion chamber mononuclear type evaporation tube structure design |
| CN111780161B (en) * | 2019-04-04 | 2022-03-25 | 中国航发湖南动力机械研究所 | Turbine engine combustion chamber |
| CN112815357A (en) * | 2020-12-24 | 2021-05-18 | 北航（四川）西部国际创新港科技有限公司 | Flame tube structure of combustion chamber and combustion chamber |
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