CN113932253A - Combustion chamber head, combustion chamber, gas turbine engine, and combustion control method - Google Patents
Combustion chamber head, combustion chamber, gas turbine engine, and combustion control method Download PDFInfo
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- CN113932253A CN113932253A CN202010608402.5A CN202010608402A CN113932253A CN 113932253 A CN113932253 A CN 113932253A CN 202010608402 A CN202010608402 A CN 202010608402A CN 113932253 A CN113932253 A CN 113932253A
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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
- F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N5/00—Systems for controlling combustion
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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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Abstract
The invention relates to a combustion chamber head, a combustion chamber, a gas turbine engine and a combustion control method. Wherein the combustor head includes a primary combustion stage including a primary combustion stage nozzle and a primary combustion stage channel providing a first air flow path; a pre-combustion stage comprising a pre-combustion stage nozzle; the stage section comprises a stage section wall surface, two ends of the stage section wall surface are respectively connected with the main combustion stage and the pre-combustion stage, and the stage section provides a second air flow path; wherein the pre-combustion stage nozzle is a centrifugal nozzle; the main combustion stage channel is provided with a main combustion stage swirler, and the oil injection direction of the main combustion stage nozzle faces the main combustion stage channel; a major portion of the air entering the combustion chamber head is mixed with fuel through a first air flow path, and a minor remaining portion is passed through a second air flow path to cool the pre-combustion stage nozzle and the stage section wall.
Description
Technical Field
The invention relates to the field of gas turbine engines, in particular to a combustion chamber head, a combustion chamber, a gas turbine engine and a combustion control method.
Background
The basic performance and structural distribution of modern aeroengine combustion chambers have reached a relatively high level, and the trend is that the axial length of the combustion chamber is continuously shortened, the head height of the combustion chamber is continuously increased, and the combustion chamber is developed in a short annular shape. No matter for military use aeroengine or civil aeroengine, combustor head air input is big, and the major link of burning tissue is basically realized at combustor head radial distance, and this pneumatic design's key lies in oil gas tissue matching, and the latter has very big influence to combustion efficiency, export temperature distribution, pollution discharge, combustion stability etc..
In order to adapt to a wide working range (the inlet temperature of the combustion chamber is up to 900K, and the inlet pressure of the combustion chamber is up to 40atm), the combustion chamber adopts a plurality of air inlets at the head part and a plurality of fuel injections (fuel fractional injection and single-stage multi-position injection) to form a multi-swirl flame. A typical technical scheme is that the central air is classified, a pre-combustion stage is arranged at the center of the head of a combustion chamber, and a main combustion stage is arranged at the outer edge of the center, so that the central pre-combustion stage is adopted to spray fuel oil with small flow to work in a diffusion combustion mode under the working condition of small thrust, and the requirements of combustion efficiency, ignition performance and the like are met; and the pre-combustion stage and the main combustion stage are adopted to simultaneously inject fuel oil under the working condition of medium and high thrust, wherein most of the fuel oil is injected into the combustion chamber through the main combustion stage and then works in a partial pre-mixing combustion mode, so that the flame temperature is controlled to reduce the emission of nitrogen oxides (NOx) and improve the outlet temperature distribution.
However, the inventor finds that the air classification technical scheme in the prior art brings great challenges to the design of the combustion chamber for adapting to different working conditions, and needs to consider the matching of multiple air swirls and the local stoichiometric conditions of fuel and air, such as: the outer layer swirling air can block the central nozzle from injecting fuel oil outwards under low thrust; the problems of uneven outlet temperature distribution, oscillatory combustion and the like caused by mutual influence of staged flames under high thrust.
Therefore, there is a need in the art for a combustor head to optimize airflow movement of the combustor head, to improve the aerodynamic and combustion stability of the combustor under different conditions, and to improve the combustion efficiency of the combustor, thereby reducing the oil consumption of the gas turbine engine, and improving the stability and reliability of the operation of the gas turbine engine.
Disclosure of Invention
It is an object of the present invention to provide a combustion chamber head.
It is another object of the present invention to provide a combustion chamber.
It is a further object of the present invention to provide a gas turbine engine.
It is a further object of the present invention to provide a combustion control method.
A combustion chamber head according to one aspect of the invention comprises:
a primary combustion stage comprising a primary combustion stage nozzle and a primary combustion stage channel providing a first air flow path; a pre-combustion stage comprising a pre-combustion stage nozzle; the stage section comprises a stage section wall surface, two ends of the stage section wall surface are respectively connected with the main combustion stage and the pre-combustion stage, and the stage section provides a second air flow path; wherein the pre-combustion stage nozzle is a centrifugal nozzle; the main combustion stage channel is provided with a main combustion stage swirler, and the oil injection direction of the main combustion stage nozzle faces the main combustion stage swirler; a major portion of the air entering the combustion chamber head is mixed with fuel through a first air flow path, and a minor remaining portion is passed through a second air flow path to cool the pre-combustion stage nozzle and the stage section wall.
In one or more embodiments of the combustor head, the outlet end of the primary combustion stage passage is downstream of the outlet end of the pre-combustion stage nozzle, and the stage section wall surface has one end connected to the outlet end of the pre-combustion stage nozzle and another end connected to the outlet end of the primary combustion stage passage, forming a tapered wall surface that flares from an upstream end to a downstream end of the stage section wall surface.
In one or more embodiments of the combustor head, the wall surface of the stage section has a plurality of cooling holes; the cooling holes are arranged to form a plurality of cooling hole rings distributed along the axial direction, and the cooling holes of each cooling hole ring are distributed around the axis of the pre-combustion stage.
In one or more embodiments of the combustor head, the main stage nozzle includes an oil collection chamber and an injection hole, and an injection direction of the injection hole is aligned with the swirl vanes of the main stage swirl body.
In one or more embodiments of the combustion chamber head, the injection holes are located in an outer wall of the oil collection chamber, the outer wall of the oil collection chamber providing an inner wall of the primary combustion stage channel; the second air flow path includes a first cooling air flow path provided between an inner wall of the oil collection chamber and the pre-stage nozzle, providing a source of air to cool the stage section wall.
In one or more embodiments of the combustor head, the pre-stage nozzle comprises a nozzle swirl core, a nozzle housing surrounding the nozzle swirl core, and a nozzle cap surrounding the nozzle housing, one end of the stage section wall surface being connected to the nozzle cap; the second air flow path includes a second cooling flow path provided between the nozzle housing and the nozzle cap, providing an air supply to cool the pre-combustion stage nozzle.
In one or more embodiments of the combustor head, the combustor head further comprises a main stage fuel pipe connected to the main stage fuel nozzle and a pre-stage fuel pipe connected to the pre-stage fuel nozzle.
A combustion chamber according to another aspect of the invention comprises a combustion chamber head as described in any one of the above.
A gas turbine engine according to a further invention of the present invention comprises a combustor head as described in any one of the above
A combustion control method according to still another aspect of the present invention is a combustion control method for a combustor of a gas turbine engine, including:
most of air forms air rotational flow through a main combustion stage channel organization at the periphery of the combustion chamber head to be used as combustion air inlet, and a small part of air passes through a stage section of the combustion chamber head to be used for cooling a pre-combustion stage nozzle and an inter-stage wall between a main combustion stage and a pre-combustion stage;
the main combustion stage nozzle sprays fuel oil into the main combustion stage channel, and the pre-combustion stage nozzle directly sprays the fuel oil into the flame tube.
In one or more embodiments of the combustion control method, under medium and small working conditions, fuel sprayed by the pre-combustion stage nozzle is mixed and combusted with air of a main combustion stage in a central backflow zone, the fuel sprayed by the main combustion stage nozzle hits swirler vanes of a main combustion stage passage, a fuel liquid film is formed on the surfaces of the vanes, secondary atomization is performed at the tail ends of outlets of the vanes, an oil-gas mixture is formed at the outlet of the main combustion stage, and then the fuel enters the central backflow zone to be combusted; under large working conditions, fuel oil sprayed by the pre-combustion stage nozzle is mixed and combusted with air of a main combustion stage in the central backflow zone, the fuel oil sprayed by the main combustion stage nozzle is directly atomized and evaporated, an oil-gas mixture is formed in the main combustion stage channel, and then the fuel oil enters the central backflow zone for combustion.
The beneficial effects of the invention include but are not limited to one or the combination of the following:
1. the main combustion stage channel is provided with the swirler, and the pre-combustion stage directly injects fuel oil, so that most of air only enters the flame tube from the main combustion stage swirler, and the flame tube forms a unique backflow zone structure with a dominant effect, thereby avoiding shearing and pulsation characteristics between air swirling flow and air swirling flow caused by air intake of multiple swirlers, and ensuring that the central backflow zone has a simple structure and stable flow.
2. The shear layer and the falling vortex formed by multiple rotational flows at the head are reduced, and the oscillatory combustion caused by flow pulsation can be eliminated.
3. The unique effective air inlet area of the head of the main combustion stage is only the main combustion stage, the longitudinal penetration distance is not influenced by the flow rate and the pressure drop of the nozzle of the main combustion stage, the scheme is easy to scale according to the practical engine thrust stage, the times of simulation and test are reduced, the research and development test process of the combustion chamber is shortened, and the research and development test difficulty of the combustion chamber is reduced.
4. The atomization of the centrifugal nozzle with the precombustion stage positioned at the center is realized through the swirl core inside the nozzle, the complex processes of secondary atomization, mixing and the like of precombustion stage fuel oil and precombustion stage swirl air do not exist, the design of the precombustion stage is simple, and the precombustion stage is not required to be considered to be matched with the precombustion stage fuel gas during design.
5. The pre-combustion stage nozzle only improves the oil-gas ratio properly under the ignition working condition, the other states can keep constant oil supply, and the fuel control strategy is simple.
6. The main combustion stage starts to work under medium and small working conditions, the air atomization effect can be enhanced by means of air shearing force under medium and low working conditions by adopting a pre-film structure, a controllable oil-gas distribution interval is formed at the outlet of the main combustion stage, and the temperature distribution of the outlet of the combustion chamber is easy to adjust.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a schematic illustration of an aircraft engine.
Fig. 2 is a schematic view of the internal structure of the combustion chamber.
FIG. 3 is a cross-sectional view of a combustion chamber head of an embodiment.
Fig. 4A and 4B are schematic external perspective structural views of a combustion chamber head according to an embodiment.
Fig. 5A and 5B are schematic structural diagrams of a cross section and an external view of a main combustion stage according to an embodiment.
Fig. 6A and 6B are schematic diagrams of fuel injection atomization in the main combustion stage under medium and small operating conditions and large operating conditions, respectively, according to an embodiment.
FIG. 7 is a cross-sectional structural schematic view of an embodiment of a pre-stage nozzle.
FIG. 8 is an exploded view of the pre-stage nozzle of FIG. 7.
FIG. 9 is a graph of velocity field simulation results for a combustor of an embodiment.
FIG. 10 is a graph of simulation results of the temperature field of the combustion chamber of an embodiment.
Detailed Description
The present invention is further described in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from those described herein, and it will be readily appreciated by those skilled in the art that the present invention can be implemented in many different forms without departing from the spirit and scope of the invention.
Also, the present application uses specific words to describe embodiments of the application, such as "one embodiment," "an embodiment," and/or "some embodiments" to mean that a particular feature, structure, or characteristic described in connection with at least one embodiment of the application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.
As shown in fig. 1, the gas turbine engine is exemplified by a turbofan engine, and includes a fan 1, a low pressure compressor 2, a high pressure compressor 3, a combustor 4, a high pressure turbine 5, a low pressure turbine 6, and a fan case 7. Air is pressurized into high-pressure air through the fan 1, the low-pressure air compressor 2 and the high-pressure air compressor 3, and the high-pressure air and fuel oil undergo a combustion reaction in the combustion chamber 4 to drive the high-pressure turbine 5 and the low-pressure turbine 6.
As shown in fig. 2, the combustion chamber 4 includes a diffuser 8, a combustion chamber outer casing 9, a combustion chamber inner casing 10, a liner outer wall 11, a liner inner wall 12, an oil rod 13, and a combustion chamber head 14. High-pressure air obtained by pressurization of the fan 1, the low-pressure compressor 2 and the high-pressure compressor 3 enters the combustion chamber 4 from the diffuser 8 after speed reduction and diffusion, and is combusted with fuel oil in a space surrounded by the outer wall 11 of the flame tube, the inner wall 12 of the flame tube and the head 14 of the combustion chamber. With continued reference to fig. 2 and 3, the combustion chamber head 14 may include a pre-stage fuel tube 15 and a main stage fuel tube 16, both secured to the combustion chamber outer casing 9 by the fuel rod 13, such that the combustion chamber head 14 is approximately cantilevered to the combustion chamber outer casing 9 by the pre-stage fuel tube 15 and the main stage fuel tube 16.
Referring to fig. 3, 4A, and 4B, in some embodiments, the combustor head 14 includes a central pre-stage 17, a peripheral main stage 19, and a stage section 18 therebetween. The pre-stage 17 includes pre-stage nozzles 170, the pre-stage nozzles 170 being swirler nozzles. The pre-stage fuel pipe 15 is connected with the pre-stage nozzle 170, and fuel 20 is conveyed to the pre-stage nozzle 170 and is directly injected into the flame tube. The primary fuel stage 19 includes a primary fuel stage nozzle 190 and a primary fuel stage passage 191, and the primary fuel stage oil conduit 16 connects the primary fuel stage nozzle 190 and delivers the fuel 21 to the primary fuel stage nozzle 190. The primary combustion stage channel 191 provides the first air flow path 25, the primary combustion stage channel 191 includes a channel inner wall 27 and a channel outer wall 28, and the primary combustion stage channel 191 is provided with a swirler 29. The stage section 18 includes a stage section wall surface 180, both ends of the stage section wall surface 180 are respectively connected with the pre-combustion stage nozzle 170 and the main combustion stage channel 191, and the stage section 18 provides the second air flow path 22. As shown in FIG. 3, the majority of the air entering the combustor head passes through the first air flow path 25 to be combined with the fuel, while the remaining minority passes through the second air flow path 22, the second air flow path 22 including second air flow path branches 23, 24, cooling the pre-stage nozzle 170 via the second air flow path branch 23, and cooling the stage wall 180 via the second air flow path branch 24, respectively. Generally speaking, the term "most" used above refers to 80% -95%, the term "the rest of the term" refers to 5% -20%, the above embodiment arranges the combustor head 14 with the cyclone flow movement at the main combustion stage, and the fuel is directly injected at the central pre-combustion stage, so that most of the air is only guided into the combustor from the cyclone 29 of the main combustion stage at the periphery of the combustor head 14, i.e. the air can be regarded as a one-way cyclone; a pre-combustion nozzle is arranged at the center of the head part, and fuel oil is directly sprayed into the combustion chamber to carry out diffusion combustion; in the main combustion stage, the oil injection direction of the nozzle of the main combustion stage faces to the main combustion stage channel, oil-gas atomization and mixing are carried out on the fuel oil in the main combustion stage channel, and partial premixed combustion is realized at the downstream of the outlet of the main combustion stage.
The technical effects of the above embodiments can be seen with reference to fig. 9 and 10, where fig. 9 is a basic form of a flow field of a combustion chamber. The central recirculation zone of the whole combustion chamber is formed by the outlet air swirl of the main combustion stage, and the axial velocity contour line is a 0 area in FIG. 9. Under the flow structure, air is sucked into the central area of the combustion chamber through the main combustion stage swirler 29, a stable single backflow area vortex is formed in the flow field, the whole vortex system structure is tightly stabilized at the front and the back of the pre-combustion stage nozzle 170, the central backflow area penetrates through the pre-combustion stage outlet and the main combustion stage outlet of the combustion chamber, fuel oil at each stage is mixed and combusted, meanwhile, the shearing and pulsation characteristics between air swirl and air swirl brought by air intake of multiple swirlers are avoided, and the central backflow area is simple in structure and stable in flow.
Fig. 10 is a schematic view of the temperature distribution when fuel is burned in the combustion chamber. When the pre-combustion stage is injected simultaneously with the main combustion stage fuel, a stable flame combustion zone is formed in the central recirculation zone downstream of the combustor head 14, which includes the diffusion flame formed by the fuel injection of the pre-combustion stage and the main combustion stage premixed fuel gas entrained by the main combustion stage swirler 29, and the two are merged together to form a unified combustion zone. Therefore, the unique backflow zone and the combustion flame structure which are dominant in action in the flame tube enable the temperature of the combustion flame to be uniform, reduce shear layers and falling vortexes formed by multiple swirling flows at the head part, and simultaneously eliminate oscillatory combustion caused by oil-gas ratio pulsation caused by respective combustion of the main and pre-combustion layers. This is more advantageous in the structure shown in fig. 3 in which the combustor head 14 is approximately cantilevered to the combustor outer casing 9 through the pre-stage fuel pipe 15 and the main-stage fuel pipe 16, and the elimination of the oscillatory combustion makes it possible to reduce the vibration received by the combustor head 14 during operation, to extend the fatigue life of the cantilevered structure, and to make the combustor operate stably and reliably. In addition, the only effective air inlet area of the main combustion stage head 14 is only the main combustion stage 19, the longitudinal penetration distance is not influenced by the flow rate and the pressure drop of the main combustion stage nozzle, the model scheme is easy to scale according to the actual engine thrust stage, the times of simulation and test are reduced, the research and development test process of the combustion chamber is shortened, and the research and development test difficulty of the combustion chamber is reduced.
With continued reference to fig. 3 and 4B, the specific configuration of the stage section 18 may be such that the outlet end of the main combustion stage channel 191 is located downstream of the outlet end of the pre-combustion stage nozzle 170, one end of the stage section wall 180 is connected to the outlet end of the pre-combustion stage nozzle 170, and the other end is connected to the outlet end of the main combustion stage channel 191, thus forming a tapered wall that flares from the upstream end to the downstream end of the stage section wall 180. The beneficial effect who so sets up lies in, can further stabilize the single backward flow district swirl that main burning level air formed, and its principle lies in, and toper wall structure has played the effect of increase backward flow district opening angle to increase the length, the width and the backward flow volume in backward flow district. In some embodiments, as shown in FIG. 4B, the stage section wall surface 180 also has a plurality of cooling holes 1801, the plurality of cooling holes 1801 are arranged to form a plurality of cooling holes 1802 distributed in the axial direction, and the cooling holes 1801 of each cooling hole 1802 are distributed around the axis of the pre-combustion stage 17, so that the stage section wall surface 180 can be effectively cooled. As shown in fig. 3, the second air flow path branch 24 of the second air flow path 22 provides a source of cooling air to the cooling holes 1801 of the stage section wall 180, i.e., the second air flow path branch 24 is a second cooling air flow path.
Referring to fig. 3, 7 and 8, the pre-combustion stage nozzle 170 includes a nozzle swirl core 35, a nozzle housing 36 surrounding the nozzle swirl core 35, and a nozzle cover 37 surrounding the nozzle housing 36, one end of a stage section wall surface 180 is connected to the nozzle cover 37, and the nozzle cover 37 and the nozzle housing 36 are connected and fixed by a bracket 38. As shown in fig. 3, the second air flow path branch 23 of the second air flow path 22 is located between the nozzle casing 36 and the nozzle cap 37, providing a source of air for cooling the pre-stage nozzle 170, i.e. the second air flow path branch 23 is the first cooling air flow path. The beneficial effect that so sets up lies in, centrifugal pre-burning stage nozzle 170's nozzle atomization is realized through the inside whirl core of nozzle, need not to set up pre-burning stage swirler and makes the secondary atomizing of pre-burning stage fuel and pre-burning stage whirl air, complicated processes such as mixture, and the design of pre-burning stage is simple, need not consider during the design that pre-burning stage oil gas matches. Meanwhile, the first cooling air flow path can prevent the outlet end of the pre-combustion stage nozzle 170 from coking, carbon deposition and the like.
Referring to fig. 3, 5 and 6A, 6B, in some embodiments, the main stage nozzle 190 includes an oil collection chamber 26 and injection holes 30, the injection holes 30 having injection directions aligned with the swirler vanes of the main stage swirler 29. With such an arrangement, as shown in fig. 6A and 6B, after the ignition of the combustion chamber is successful, the main combustion stage nozzle 190 starts to perform oil injection operation along with the gradual increase of the working condition, and when the inlet air pressure and temperature of the combustion chamber are not very high in a medium-small working condition, as shown in fig. 6A, the fuel oil 31 injected from the injection hole 30 of the main combustion stage nozzle 190 directly hits the surface of the swirler vane due to the low injection pressure, and at this time, the function of the swirler vane can be regarded as a prefilming plate, the fuel oil forms an oil film 32 on the vane surface, and then the oil film 32 is broken into an oil mist 33 under the pneumatic shearing action of the main combustion stage air 25, and through the prefilming atomization process, the dispersion uniformity of the fuel oil under the medium-low working condition can be improved. When the operating condition is further increased, in a large operating condition, as shown in fig. 6B, the air pressure and temperature at the inlet of the combustion chamber are further increased, at this time, the fuel injection pressure is increased, the fuel injected from the injection hole 30 is directly atomized and evaporated to form fuel vapor 34, at this time, an oil film is not formed on the surface of the swirl vanes, and at this time, the swirl vanes function to guide the mixed fuel vapor. Therefore, by adopting the main combustion stage nozzle 190 introduced above, the main combustion stage starts to work under medium and small working conditions, the air atomization effect can be enhanced by means of air shearing force under medium and low working conditions by adopting a pre-film structure, a controllable oil-gas distribution interval is formed at the outlet of the main combustion stage, and the temperature distribution of the outlet of the combustion chamber is easy to adjust. According to the arrangement, the main combustion stage 17 starts to work under medium and small working conditions, the air atomization effect is enhanced by means of air shearing force under the medium and small working conditions, a controllable oil-gas distribution interval is formed at the outlet of the main combustion stage, the temperature distribution of the outlet of the combustion chamber is easy to adjust, the main combustion stage 17 starts to work under the medium and small working conditions, the pre-combustion stage nozzle 170 only needs to properly improve the oil-gas ratio under the ignition working condition, constant oil supply can be kept under other working conditions, the fuel oil control strategy is simple, and the combustion algorithm design of a control system of the gas turbine engine is simplified.
With continued reference to fig. 3 and 5A, in some embodiments, the specific configuration of the oil collection chamber 26 and the injection holes 30 may be such that the injection holes 30 are located on an outer wall of the oil collection chamber 26, the outer wall of the oil collection chamber 26 providing the inner wall 27 of the primary combustion stage channel 191; the provision of the second air flow path branch 24 of the second air flow path 22, i.e., the provision of the first cooling air flow path, between the inner wall 260 of the oil collection pocket 26 and the pre-stage nozzle 170 provides a source of air for cooling the stage section wall 180, thus resulting in a compact configuration of the combustion chamber head 14 and saving of space for the combustion chamber in the engine.
As introduced above, a combustion control method for a combustor of a gas turbine engine may include:
most of the air passes through the main combustion stage channel 191 at the periphery of the combustion chamber head 14 to form air swirl as combustion air, and a small part of the air passes through the stage section 18 of the combustion chamber head 14 to be used for cooling the pre-combustion stage nozzle 170 and the stage section wall surface 180;
the main combustion stage nozzle 190 injects fuel into the main combustion stage passage 191, and the pre-combustion stage nozzle 170 injects fuel directly into the liner to achieve diffusion combustion downstream of the pre-combustion stage outlet and partial pre-mixing combustion downstream of the main combustion stage outlet.
Specifically, in some embodiments, under medium and small operating conditions, the pre-combustion stage nozzle 170 sprays fuel, the fuel 31 sprayed from the main combustion stage nozzle 190 hits swirler vanes of the main combustion stage passage 191 to form a liquid film, and then secondary atomization is performed, an oil-gas mixture is formed at the outlet of the main combustion stage, and then the oil-gas mixture enters the central recirculation zone for combustion; under large operating conditions, the fuel from the pre-stage nozzle 170 is atomized and evaporated directly into fuel vapor 34, forming an air-fuel mixture in the main stage channel, and then enters the central recirculation zone for combustion. So can make the main burning stage also can realize good fuel atomization effect under well little operating mode to make the main burning stage can begin to work under well little operating mode, its principle lies in, adopts the prefilming structure can strengthen air atomization effect with the help of air shear force under well little operating mode, and forms controllable oil gas distribution interval at the main burning stage export, easily adjusts combustion chamber export temperature distribution.
The beneficial effects of the combustion chamber head and the combustion control method described in the above embodiments include, but are not limited to:
1. the main combustion stage channel is provided with the swirler, and the pre-combustion stage directly injects fuel oil, so that most of air only enters the flame tube from the main combustion stage swirler, and the flame tube forms a unique backflow zone structure with a dominant effect, thereby avoiding shearing and pulsation characteristics between air swirling flow and air swirling flow caused by air intake of multiple swirlers, and ensuring that the central backflow zone has a simple structure and stable flow.
2. The shear layer and the falling vortex formed by multiple rotational flows at the head are reduced, and the oscillatory combustion caused by flow pulsation can be eliminated.
3. The unique effective air inlet area of the head of the main combustion stage is only the main combustion stage, the longitudinal penetration distance is not influenced by the flow rate and the pressure drop of the nozzle of the main combustion stage, the scheme is easy to scale according to the practical engine thrust stage, the times of simulation and test are reduced, the research and development test process of the combustion chamber is shortened, and the research and development test difficulty of the combustion chamber is reduced.
4. The atomization of the centrifugal nozzle with the precombustion stage positioned at the center is realized through the swirl core inside the nozzle, the secondary atomization, mixing and other complex processes of the precombustion stage fuel oil and the precombustion stage swirl air are avoided, the design of the precombustion stage is simple, and the precombustion stage fuel-air matching is not considered during the design.
5. The pre-combustion stage nozzle only improves the oil-gas ratio properly under the ignition working condition, the other states can keep constant oil supply, and the fuel control strategy is simple.
6. The main combustion stage starts to work under medium and small working conditions, the air atomization effect can be enhanced by means of air shearing force under medium and low working conditions by adopting a pre-film structure, a controllable oil-gas distribution interval is formed at the outlet of the main combustion stage, and the temperature distribution of the outlet of the combustion chamber is easy to adjust.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (11)
1. A combustion chamber head, comprising
A primary combustion stage comprising a primary combustion stage nozzle and a primary combustion stage channel providing a first air flow path;
a pre-combustion stage comprising a pre-combustion stage nozzle; and
the stage section comprises a stage section wall surface, two ends of the stage section wall surface are respectively connected with the main combustion stage and the pre-combustion stage, and the stage section provides a second air flow path;
wherein the pre-combustion stage nozzle is a centrifugal nozzle; the main combustion stage channel is provided with a main combustion stage swirler, and the oil injection direction of the main combustion stage nozzle faces the main combustion stage swirler; a major portion of the air entering the combustion chamber head is mixed with fuel through a first air flow path, and a minor remaining portion is passed through a second air flow path to cool the pre-combustion stage nozzle and the stage section wall.
2. The combustor head of claim 1, wherein the outlet end of the primary combustion stage passage is located downstream of the outlet end of the pre-combustion stage nozzle, and wherein the stage section wall has one end connected to the outlet end of the pre-combustion stage nozzle and another end connected to the outlet end of the primary combustion stage passage forming a tapered wall that flares from an upstream end to a downstream end of the stage section wall.
3. The combustion chamber head as set forth in claim 2 wherein the wall surface of the stage section has a plurality of cooling holes; the cooling holes are arranged to form a plurality of cooling hole rings distributed along the axial direction, and the cooling holes of each cooling hole ring are distributed around the axis of the pre-combustion stage.
4. The combustor head of claim 1, wherein the main stage nozzle comprises an oil collection chamber and an injection orifice directed at swirl vanes of the main stage swirl body.
5. The combustion chamber head of claim 4 wherein said injection holes are located in an outer wall of said oil collection chamber, said outer wall of said oil collection chamber providing an inner wall of said primary combustion stage channel; the second air flow path includes a first cooling air flow path provided between an inner wall of the oil collection chamber and the pre-stage nozzle, providing a source of air to cool the stage section wall.
6. The combustor head of claim 1, wherein the pre-combustion stage nozzle comprises a nozzle swirl core, a nozzle housing surrounding the nozzle swirl core, and a nozzle cap surrounding the nozzle housing, the stage section wall surface being connected at one end to the nozzle cap; the second air flow path includes a second cooling flow path provided between the nozzle housing and the nozzle cap, providing an air supply to cool the pre-combustion stage nozzle.
7. The combustor head of claim 1, further comprising a main stage fuel tube connected to the main stage fuel nozzle and a pre-stage fuel tube connected to the pre-stage fuel nozzle.
8. A combustion chamber comprising a combustion chamber head according to any one of claims 1 to 7.
9. A gas turbine engine comprising a combustor head as claimed in any one of claims 1 to 7.
10. A combustion control method for a combustor of a gas turbine engine, comprising:
most of air forms air rotational flow through a main combustion stage channel organization at the periphery of the combustion chamber head to be used as combustion air inlet, and a small part of air passes through a stage section of the combustion chamber head to be used for cooling a pre-combustion stage nozzle and an inter-stage wall between a main combustion stage and a pre-combustion stage;
the main combustion stage nozzle sprays fuel oil into the main combustion stage channel, and the pre-combustion stage nozzle directly sprays the fuel oil into the flame tube.
11. The combustion control method as claimed in claim 10, characterized by comprising:
under medium and small working conditions, fuel oil sprayed by the pre-combustion stage nozzle is mixed and combusted with air of a main combustion stage in a central backflow zone, the fuel oil sprayed by the main combustion stage nozzle is impacted on swirler vanes of a main combustion stage channel, a fuel oil liquid film is formed on the surfaces of the vanes, secondary atomization is carried out at the tail ends of outlets of the vanes, an oil-gas mixture is formed at the outlets of the main combustion stage, and then the mixture enters the central backflow zone for combustion;
under large working conditions, fuel oil sprayed by the pre-combustion stage nozzle is mixed and combusted with air of a main combustion stage in the central backflow zone, the fuel oil sprayed by the main combustion stage nozzle is directly atomized and evaporated, an oil-gas mixture is formed in the main combustion stage channel, and then the fuel oil enters the central backflow zone for combustion.
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