CN113864823B - Turbine engine cyclic heating multistage combustion system - Google Patents
Turbine engine cyclic heating multistage combustion system Download PDFInfo
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- CN113864823B CN113864823B CN202111322217.0A CN202111322217A CN113864823B CN 113864823 B CN113864823 B CN 113864823B CN 202111322217 A CN202111322217 A CN 202111322217A CN 113864823 B CN113864823 B CN 113864823B
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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
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
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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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
Abstract
The invention discloses a turbine engine circulation heating multistage combustion system, which comprises an air inlet channel penetrating through a flame tube shell, wherein the flame tube shell comprises a preheating heat-insulating layer and a fuel premixing layer, the interior of the preheating heat-insulating layer is of a mutually communicated honeycomb structure, a fuel main pipe is wound outside the preheating heat-insulating layer, the tail end of the fuel main pipe penetrates through the preheating heat-insulating layer and is communicated with the honeycomb structure inside, a fuel channel is arranged between the preheating heat-insulating layer and the fuel premixing layer, the outer side of the fuel channel is provided with an inlet communicated with the honeycomb structure, the inner side of the fuel channel is provided with a fuel nozzle spraying to a combustion chamber, the combustion chamber comprises a pre-combustion section, a contraction section and an expansion section, and an air nozzle connected with the air inlet channel is arranged in the combustion chamber. The invention can ensure the combustion efficiency, has stable and efficient combustion, uniform temperature distribution, lower generated noise and pollutant discharge and long service life and reliability.
Description
Technical Field
The invention relates to the technical field of turbine engine combustion, in particular to a turbine engine circulating heating multistage combustion system.
Background
The fuel Turbine engine is called a fuel Turbine for short, and in the main flow of air and fuel, the fuel Turbine only has a fuel Turbine cycle consisting of three major components, namely a Compressor (Compressor), a Combustor (Combustor) and a fuel Turbine (Turbine), which is generally called a simple cycle. The temperature of a flame tube in a combustion chamber of the fuel turbine during working is high, the working environment is quite severe, and materials cannot work for a long time under the severe environment far exceeding the normal working temperature, so that the flame tube in the combustion chamber must be cooled to prevent the flame tube from cracking or being burnt out to reduce the service life of an engine.
However, the improvement of the cycle efficiency of the fuel turbine mainly depends on the increase of the exhaust temperature of the combustion chamber, the temperature in the combustion chamber is inevitably increased when the exhaust temperature of the combustion chamber is increased, the discharge of oxynitride in the combustion chamber is increased, and the working environment of the combustion chamber is also worsened, such as high pressure, large heat load, high temperature and high speed, and complicated flow field. When the temperature of the combustion chamber rises, cooling the liner not only reduces combustion efficiency, but also causes heat loss.
Therefore, in the prior art, on the basis of ensuring high combustion efficiency of a combustion chamber, how to improve the performance of a fuel turbine and reduce the pollution of emissions is a difficult point to be solved.
Disclosure of Invention
Aiming at the defects in the background technology, the invention provides a turbine engine circulation heating multistage combustion system, which solves the technical problem that the combustion efficiency, the emission and the structural life of the existing fuel turbine engine cannot be improved simultaneously.
The technical scheme of the invention is realized as follows: the turbine engine circulation heating multistage combustion system comprises a flame tube shell, an air inlet channel extending to a combustion chamber is arranged through the flame tube shell, the flame tube shell comprises an external preheating heat-insulating layer and an internal fuel premixing layer, the internal part of the preheating heat-insulating layer is of a mutually communicated honeycomb structure, a fuel main pipe is arranged at the front end of the preheating heat-insulating layer, the fuel main pipe is wound on the outer wall of the preheating heat-insulating layer, the tail end of the fuel main pipe penetrates through the preheating heat-insulating layer and is communicated with the internal honeycomb structure, a fuel channel is arranged between the preheating heat-insulating layer and the fuel premixing layer, the rear end of the fuel channel is closed, the front end of the fuel channel is provided with a front air inlet channel communicated with a compressor, the outer side of the fuel channel is provided with an inlet communicated with the honeycomb structure, the inner side of the fuel channel is provided with a fuel nozzle spraying to the combustion chamber, and the combustion chamber comprises a pre-burning section, a contraction section and an expansion section, and an air nozzle connected with the air inlet channel is arranged in the combustion chamber, the air nozzle and the fuel nozzle are arranged in pairs in the pre-combustion section, the contraction section and the expansion section, and the length of the expansion section is greater than the sum of the lengths of the pre-combustion section and the contraction section.
Furthermore, the front air inlet channel comprises a honeycomb-shaped communication section at the front part, the honeycomb-shaped communication section is connected with the air nozzle, and a capillary channel is arranged between the honeycomb-shaped communication section and the fuel channel.
Furthermore, the contraction section comprises a radial contraction structure protruding inwards, the cross section of the radial contraction structure is semicircular, a plurality of branch pipelines connected with the fuel channel are arranged in the semicircle, and the tail ends of the two branch pipelines are connected with the same fuel nozzle.
Further, a ring of fuel nozzles is arranged along the circumferential direction of the pre-burning section and the contraction section, three rings of fuel nozzles are arranged along the circumferential direction of the expansion section, the number of the fuel nozzles of each ring in the expansion section is equal to that of the fuel nozzles of each ring in the pre-burning section, and the number of the fuel nozzles in the contraction section is larger than that of the fuel nozzles in the pre-burning section.
Further, the front end of preheating the heat preservation is provided with the bellied section of arch to the periphery, and the front end of fuel house steward penetrates after passing through the bellied section and preheating the heat preservation and wears out, and the position that the fuel house steward penetrated the bellied section is provided with the intercommunicating pore that communicates with inside honeycomb structure.
Furthermore, the part of the fuel main pipe extending out after penetrating through the convex section is a semicircular pipe, and the semicircular pipe is uniformly arranged in a spiral shape along the axial direction of the preheating heat-insulating layer.
Furthermore, the air inlet channel comprises an air inlet hopper arranged on the outer wall of the preheating heat-insulating layer, an air inlet branch pipe penetrating through the preheating heat-insulating layer and the fuel premixing layer is connected with the air inlet hopper, and the air nozzle is arranged at the tail end of the air inlet branch pipe.
Furthermore, the adjacent air inlet branch pipes are communicated with each other in the preheating insulation layer and the fuel premixing layer.
Furthermore, the fuel channels are arranged in parallel along the length direction of the flame tube shell and are communicated with each other.
Furthermore, a plurality of feeding branch pipes inserted into the preheating heat-insulating layer are arranged between the front end and the rear end of the fuel main pipe, the outer ends of the feeding branch pipes are communicated with the fuel main pipe, and the inner ends of the feeding branch pipes are communicated with the honeycomb structure.
The beneficial effects of the invention include:
(1) the invention can be burned in stages, in the pre-burning section, the fuel is firstly premixed with the air pressed by the air compressor before entering the pre-burning section, the premixed fuel is sprayed out from a small amount of fuel nozzles in the pre-burning section and is mixed with the air sprayed out from the air nozzle together with the fuel sprayed out from the central nozzle of the flame tube, and the preliminary burning is carried out in the pre-burning section, the air-fuel ratio is larger in the process, the burning belongs to the lean mixture, the gas is more and the oil is less, the burning is complete, the oil consumption is low, the pollution is less, the total amount of the fuel is less, the burning temperature is reduced on the premise of full burning, the burden of a burning chamber is lightened, and the nitrogen oxygen and the hydrocarbon compounds in the rich oil burning zone can also be reduced; in the contraction section, the space is reduced, the fuel is converged from the two branch pipelines to the same fuel nozzle at a high speed, the products in the pre-combustion section can be quickly and temporarily extinguished by the fuel and air injected at the high speed, but the reaction path and time are short, namely the high nitrogen oxide generation process is extremely short, and the generated nitrogen oxides are less; in the expansion section, the injected fuel oil and air are mixed with the rich fuel in the contraction section for afterburning, so that the combustion is stable and efficient, the temperature distribution is uniform, and the generated noise and pollutant emission are lower;
(2) the air entering the front air inlet passage from the air compressor can be fully premixed with fuel in the pre-combustion section, can also be partially premixed with the fuel in the contraction section and the expansion section, can be preheated, can also be used for internally cooling the flame tube heated up by internal high-temperature airflow, hardly influences the high-temperature environment in the combustion chamber, can play a role in silencing, and reduces the noise generated by the air compressor supplying air to the combustion chamber.
(3) The fuel main pipe of extension is add on the flame tube shell, can also preheat fuel when cooling the flame tube shell, improves combustion efficiency. Further, preheat the heat preservation and set up to inside honeycomb structure for mutual intercommunication, fuel house steward gets into through feeding branch pipe and preheats in the heat preservation, not only realizes preheating the outside of fuel through the flame tube shell, has realized inside preheating to fuel through inner structure simultaneously, makes the abundant evaporation of fuel and reaches supercritical state, viscidity step-down, the diffusion capacity reinforcing, and then can be with air mixing's more abundant even, fully improved combustion efficiency, reduced the pollutant discharge.
(4) The fuel and the air regulate and control the temperature of the whole flame tube from inside to outside, the fuel channel is arranged between the preheating heat-insulating layer and the fuel premixing layer, the sufficiency of preheating and cooling is ensured, excessive heat loss is avoided, the honeycomb structure in the preheating heat-insulating layer enables the fuel to be fully exchanged and preheated, a metal-fuel composite heat-insulating layer is formed, the combustion chamber and the preheating heat-insulating layer are isolated by the fuel premixing layer in the inner part, and the structural reliability is also ensured while the heat is locked.
Drawings
In order to illustrate the embodiments of the invention more clearly, the drawings that are needed in the description of the embodiments will be briefly described below, it being apparent that the drawings in the following description are only some embodiments of the invention, and that other drawings may be derived from those drawings by a person skilled in the art without inventive effort.
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic cross-sectional view of the present invention;
FIG. 3 is a left side view of the present invention;
in the figure:
1-preheating heat-insulating layer, 2-fuel premixing layer,
3-a fuel header pipe, 31-a communication hole, 32-a semicircular pipe,
4-fuel channel, 41-inlet, 42-branch pipe;
5-front air inlet channel, 51-honeycomb communicating section, 52-capillary channel;
7-combustion chamber, 8-fuel nozzle;
9-an air inlet hopper, 91-an air nozzle;
10-precombustion section, 11-contraction section, 12-expansion section and 13-bulge section;
101-radially contracted configuration.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without inventive effort based on the embodiments of the present invention, are within the scope of the present invention.
A multi-stage combustion system for circulating heating of a turbine engine is shown in figures 1-3 and comprises a flame tube shell, wherein the flame tube shell comprises an external preheating and insulating layer 1 and an internal fuel premixing layer 2, and the preheating and insulating layer 1 and the internal fuel premixing layer 2 can be processed and manufactured through a 3D printing technology. Specifically, the interior of the preheating and insulating layer 1 is a mutually communicated honeycomb structure, the interior structure is similar to a honeycomb structure but is mutually communicated, and after the gas enters, the gas can flow back and forth and can flow towards an outlet under certain pressure.
The front end of preheating heat preservation 1 is provided with fuel main 3, and fuel main 3 twines on preheating heat preservation 1's outer wall, can be heated by preheating heat preservation 1's outer wall when fuel flows through fuel main 3, and then reduces the viscosity of fuel, strengthens the mobility of fuel. The tail end of the fuel main pipe 3 penetrates into the preheating heat-insulating layer 1 and is communicated with the internal honeycomb structure, fuel heated by the outer wall of the preheating heat-insulating layer 1 can enter the honeycomb internal part of the preheating heat-insulating layer 1, and the fuel flows in the mutually communicated honeycomb structures to further heat and raise the temperature, so that the viscosity of the fuel is further reduced, and the fluidity of the fuel is enhanced.
A fuel channel 4 is arranged between the preheating heat-insulating layer 1 and the fuel premixing layer 2, the outer side of the fuel channel 4 is provided with an inlet 41 communicated with the honeycomb structure, and the inner side of the fuel channel is provided with a fuel nozzle 8 spraying to the combustion chamber 7. The fuel can be gathered in the fuel channel 4 after passing through the preheating heat-insulating layer 1 and the inside of the honeycomb structure is communicated with each other, and because the fuel channel 4 is closer to the combustion chamber 7, the fuel in the fuel channel 4 can be further heated and heated to reach a supercritical state, the viscosity of the fuel becomes low, the diffusion capacity is enhanced, and the mixing with the air can be very simply realized.
The rear end of the fuel passage 4 is closed, and the front end of the fuel passage is provided with a front air inlet passage 5 communicated with the air compressor, so that the air compressor can blow air into the front part of the fuel passage 4 through the front air inlet passage 5 to realize the premixing of the air and the fuel. An air inlet channel extending to the combustion chamber is arranged through the flame tube shell, and an air nozzle 91 connected with the air inlet channel is arranged in the combustion chamber 7. The air inlet channel comprises an air inlet hopper 9 arranged on the outer wall of the preheating heat-insulating layer 1, an air inlet branch pipe penetrating through the preheating heat-insulating layer 1 and the fuel premixing layer 2 is connected with the air inlet hopper 9, and the air nozzle 91 is arranged at the tail end of the air inlet branch pipe. The front intake passage 5 includes a front honeycomb communication section 51, and the honeycomb communication section 51 is connected to the air nozzle 91 and provided with a capillary passage 52 with the fuel passage 4. The compressor delivers a portion of the air to the forward intake passage 5, which is directly premixed with fuel, and another portion is injected through the air nozzle 91 into the combustion chamber 7.
The combustion chamber 7 comprises a precombustion section 10, a contraction section 11 and an expansion section 12, and the air nozzle 91 and the fuel nozzle 8 are arranged in pairs at the precombustion section 10, the contraction section 11 and the expansion section 12. The diameter of the precombustion section 10 and the diameter of the expansion section 12 are both larger than the diameter of the contraction section 11, the length of the expansion section 12 is larger than the sum of the lengths of the precombustion section 10 and the contraction section 11, mixed fuel entering the combustion chamber 7 through the air nozzle 91 and the fuel nozzle 8 is fully mixed and fully combusted in the precombustion section 10, the mixed fuel is extinguished temporarily in the contraction section 11, and the mixed fuel and rich fuel in the contraction section 12 are mixed and afterburned. The specific process is as follows: in the pre-combustion section, the fuel is firstly premixed with air pressed in by the air compressor before entering the pre-combustion section, the premixed fuel is sprayed out from a small amount of fuel nozzles in the pre-combustion section and is mixed with the fuel sprayed out from a central nozzle of the flame tube and the air sprayed out from the air nozzles, and preliminary combustion is carried out in the pre-combustion section, so that the air-fuel ratio is large, the combustion belongs to lean mixture, the gas and the oil are more and less, the combustion is complete, the oil consumption is low, the pollution is low, the total amount of the fuel is less, the combustion temperature is reduced on the premise of full combustion, the burden of a combustion chamber is lightened, and the nitrogen, oxygen and hydrocarbon compounds in an oil-rich combustion zone can be reduced; in the contraction section, the space is reduced, the fuel is gathered from high speed, the products in the pre-combustion section can be quickly and temporarily extinguished by the fuel and air injected at high speed, but the reaction path and time are very short, namely the high nitrogen oxide generation process is very short, and the generated nitrogen oxide is less; in the expansion section, the injected fuel oil and air are mixed with the rich fuel in the contraction section for afterburning, so that the combustion is stable and efficient, the temperature distribution is uniform, and the generated noise and pollutant emission are lower.
Specifically, the contraction section 11 comprises a radial contraction structure 101 protruding inwards, the cross section of the radial contraction structure 101 is semicircular, so that the combustion, quenching and re-combustion processes are soft, and the reliability of the structural strength is guaranteed. A plurality of branch pipelines 42 connected with the fuel channel 4 are arranged in the semicircle, the tail ends of the two branch pipelines 42 are connected with the same fuel nozzle 8, so that the fuel nozzle in the contraction section 11 can jet a large amount of fuel at high speed, the fuel combustion of the precombustion section 10 is quickly extinguished, and the support can be provided for the afterburning of the expansion section 12 at the rear part, so that the combustion is stable and efficient, and the temperature distribution is uniform. One ring of fuel nozzles 8 is arranged along the circumferential direction of the pre-combustion section 10 and the contraction section 11, three rings of fuel nozzles 8 are arranged along the circumferential direction of the expansion section 12, the number of fuel nozzles 8 of each ring in the expansion section 12 is equal to that of the fuel nozzles 8 of each ring in the pre-combustion section 10, and the number of fuel nozzles 8 in the contraction section 11 is larger than that of the fuel nozzles 8 in the pre-combustion section 10.
Further, preheat the front end of heat preservation 1 and be provided with the bellied protruding section 13 of periphery, wear out after the front end of fuel main 3 penetrates through protruding section 13 and preheats heat preservation 1, and the position that fuel main 3 penetrated protruding section 13 is provided with the intercommunicating pore 31 with the honeycomb structure intercommunication of inside for fuel can get into the inside and the outside of preheating the heat preservation simultaneously, realizes the cascaded cooling of preheating of fuel and flame tube.
Further, the part of the fuel main pipe 3 extending out after passing through the convex section 13 is a semicircular pipe 32, and the semicircular pipe 32 is spirally and uniformly arranged along the axial direction of the preheating insulation layer 1. Preheat the heat preservation and set up to inside honeycomb structure for mutual intercommunication, fuel house steward gets into through the feeding branch pipe and preheats in the heat preservation, not only realizes preheating the outside of fuel through the flame tube shell, has realized inside preheating to fuel through inner structure simultaneously, makes the abundant evaporation of fuel and reaches supercritical state, viscidity step-down, the diffusion capacity reinforcing, and then can be with the more abundant even of air mixing, fully improved combustion efficiency, reduced the pollutant discharge.
Furthermore, adjacent air inlet branch pipes are communicated with each other in the preheating heat-insulating layer 1 and the fuel premixing layer 2, a plurality of fuel passages 4 are arranged, and the plurality of fuel passages 4 are arranged in parallel along the length direction of the flame tube shell and are communicated with each other. A plurality of feeding branch pipes inserted into the preheating heat-insulating layer 1 are arranged between the front end and the rear end of the fuel main pipe 3, the outer ends of the feeding branch pipes are communicated with the fuel main pipe 3, and the inner ends of the feeding branch pipes are communicated with the honeycomb structure. So that the preheating effect on the air and the fuel is better and more uniform, and the cooling on the flame tube is better, more uniform and more sufficient. The fuel and the air regulate and control the temperature of the whole flame tube from inside to outside, the fuel channel is arranged between the preheating heat-insulating layer and the fuel premixing layer, the sufficiency of preheating and cooling is ensured, excessive heat loss is avoided, the honeycomb structure in the preheating heat-insulating layer enables the fuel to be fully exchanged and preheated, a metal-fuel composite heat-insulating layer is formed, the combustion chamber and the preheating heat-insulating layer are isolated by the fuel premixing layer in the inner part, and the structural reliability is also ensured while the heat is locked.
Nothing in this specification is intended to be exhaustive of all conventional and well known techniques.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and should not be taken as limiting the scope of the present invention, which is intended to cover any modifications, equivalents, improvements, etc. within the spirit and scope of the present invention.
Claims (10)
1. Turbine engine circulation heating multistage combustion system, including the flame tube shell, pass the flame tube shell and be provided with the inlet channel who extends to the combustion chamber, its characterized in that: the flame tube shell comprises an external preheating heat-insulating layer (1) and an internal fuel premixing layer (2), the internal preheating heat-insulating layer (1) is of a honeycomb structure communicated with each other, a fuel header pipe (3) is arranged at the front end of the preheating heat-insulating layer (1), the fuel header pipe (3) is wound on the outer wall of the preheating heat-insulating layer (1), the tail end of the fuel header pipe (3) penetrates into the preheating heat-insulating layer (1) and is communicated with the internal honeycomb structure, a fuel channel (4) is arranged between the preheating heat-insulating layer (1) and the fuel premixing layer (2), the rear end of the fuel channel (4) is sealed, the front end of the fuel channel is provided with a front air inlet channel (5) communicated with a gas compressor, the outer side of the fuel channel (4) is provided with an inlet (41) communicated with the honeycomb structure, the inner side of the fuel nozzle (8) for spraying to a combustion chamber (7) is arranged, and the combustion chamber (7) comprises a pre-burning section (10), The combustor comprises a contraction section (11) and an expansion section (12), an air nozzle (91) connected with an air inlet channel is arranged in the combustion chamber (7), the air nozzle (91) and a fuel nozzle (8) are arranged in the precombustion section (10), the contraction section (11) and the expansion section (12) in pairs, and the length of the expansion section (12) is greater than the sum of the lengths of the precombustion section (10) and the contraction section (11).
2. The turbine engine hydronic multistage combustion system of claim 1, wherein: the front air inlet channel (5) comprises a front honeycomb-shaped communicating section (51), the honeycomb-shaped communicating section (51) is connected with the air nozzle (91) and a capillary channel (52) is arranged between the honeycomb-shaped communicating section and the fuel channel (4).
3. The turbine engine hydronic multistage combustion system according to claim 1 or 2, characterized in that: the contraction section (11) comprises a radial contraction structure (101) protruding inwards, the cross section of the radial contraction structure (101) is semicircular, a plurality of branch pipelines (42) connected with the fuel channel (4) are arranged in the semicircle, and the tail ends of the two branch pipelines (42) are connected with the same fuel nozzle (8).
4. The turbine engine hydronic multistage combustion system according to claim 3, wherein: the fuel injection device is characterized in that a ring of fuel nozzles (8) are arranged in the circumferential direction of the pre-combustion section (10) and the contraction section (11), three rings of fuel nozzles (8) are arranged in the circumferential direction of the expansion section (12), the number of the fuel nozzles (8) in each ring in the expansion section (12) is equal to that of the fuel nozzles (8) in each ring in the pre-combustion section (10), and the number of the fuel nozzles (8) in the contraction section (11) is larger than that of the fuel nozzles (8) in the pre-combustion section (10).
5. The turbine engine cycle heating multistage combustion system of any of claims 1, 2, 4, wherein: the front end of preheating heat preservation (1) is provided with protruding section (13) to the periphery arch, wear out after the front end of fuel house steward (3) penetrates preheating heat preservation (1) through protruding section (13), and the position that fuel house steward (3) penetrated protruding section (13) is provided with intercommunicating pore (31) with inside honeycomb structure intercommunication.
6. The turbine engine hydronic multistage combustion system according to claim 5, wherein: the part of the fuel main pipe (3) extending out after penetrating through the convex section (13) is a semicircular pipe (32), and the semicircular pipe (32) is spirally and uniformly arranged along the axial direction of the preheating heat-insulating layer (1).
7. The turbine engine hydronic multistage combustion system according to claim 6, wherein: the air inlet passage comprises an air inlet hopper (9) arranged on the outer wall of the preheating heat-insulating layer (1), an air inlet branch pipe penetrating through the preheating heat-insulating layer (1) and the fuel premixing layer (2) is connected with the air inlet hopper (9), and the air nozzle (91) is arranged at the tail end of the air inlet branch pipe.
8. The turbine engine hydronic multistage combustion system according to claim 7, wherein: the adjacent air inlet branch pipes are communicated with each other in the preheating and insulating layer (1) and the fuel premixing layer (2).
9. The turbine engine cycle heating multistage combustion system of any of claims 1, 2, 4, 6, 7, wherein: the number of the fuel channels (4) is multiple, and the fuel channels (4) are arranged in parallel along the length direction of the flame tube shell and are communicated with each other.
10. The turbine engine hydronic multistage combustion system according to claim 9, wherein: a plurality of feeding branch pipes inserted into the preheating heat-insulating layer (1) are arranged between the front end and the rear end of the fuel main pipe (3), the outer ends of the feeding branch pipes are communicated with the fuel main pipe (3), and the inner ends of the feeding branch pipes are communicated with the honeycomb structure.
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