CN116734289A - Gas turbine engine and fuel nozzle, combustion chamber, fuel ring and oscillation combustion suppression method used therefor - Google Patents

Abstract

The invention provides a gas turbine engine, a fuel nozzle, a combustion chamber, a fuel ring and a method for suppressing oscillation combustion. The fuel nozzle includes: a fuel ring, including a ring body and a plurality of fuel injection holes. The plurality of fuel injection holes are distributed along the circumference of the ring body, and the injection direction of the plurality of fuel injection holes is radial; an annular inner wall; an annular outer wall, surrounding At least part of the annular inner wall forms an annular chamber; wherein, the plurality of fuel nozzle holes at least include nozzle hole groups with different axial positions. The nozzle hole groups are arranged on the annular body in an annular arrangement to form an axis along the annular body. Multiple coaxial annular and nozzle groups distributed in a direction may be selectively combined to form at least one combination that suppresses oscillatory combustion. Achieve suppression of oscillatory combustion.

Description

Gas turbine engines and fuel nozzles, combustion chambers, fuel rings and suppression therefor Oscillating combustion method

Technical field

The present invention relates to the field of aerospace engines, and in particular to a gas turbine engine and a fuel nozzle, a combustion chamber, a fuel ring and a method for suppressing oscillation combustion.

Background technique

The combustion chamber of modern low-pollution lean-burn engines is very prone to combustion oscillations. Combustion oscillations affect the safe and stable operation of gas turbines and aero-engines. This oscillation can further cause vibration of the engine structure, limit the increase in engine speed and load, induce flameout and backfire, and Leading to serious consequences such as engine component failure and explosion. In addition, during the development process of aero engines and gas turbines, thermoacoustic oscillation often occurs, which affects the development process of components and complete machines, delaying project development progress.

Contents of the invention

It is an object of the present invention to provide a fuel nozzle for a gas turbine engine.

Another object of the invention is to provide a combustor for a gas turbine engine.

Yet another object of the present invention is to provide a gas turbine engine.

Another object of the present invention is to provide a method for suppressing oscillatory combustion in a gas turbine engine.

It is a further object of the present invention to provide a fuel ring for a fuel turbine engine.

According to an aspect of the present invention, a fuel nozzle for a gas turbine engine includes: a fuel ring, including a ring body and a plurality of fuel injection holes, the plurality of fuel injection holes are distributed along the circumferential direction of the ring body, so The injection direction of the plurality of fuel injection holes is radial; an annular inner wall; an annular outer wall, forming an annular chamber around at least part of the annular inner wall; wherein the plurality of fuel injection holes at least include nozzles with different axial positions. Hole group, the nozzle hole group is arranged on the ring body in an annular arrangement, forming a plurality of coaxial annulus distributed along the axial direction of the ring body, the nozzle hole group can be selectively combination to form at least one combination that suppresses oscillatory combustion.

The technical solution of the present application sets nozzle groups at different axial positions, so that the fuel injected from different nozzle groups has different flight times from the injection position to the flame front, thereby increasing the gap between the heat release rate pulsation and the pressure pulsation. The delay time distribution range reduces the probability of in-phase forward coupling of fuel combustion heat release rate pulsation and pressure pulsation in the combustion chamber, reduces the risk of combustion oscillation, and plays a preventive role. At the same time, different nozzle groups can be selectively combined to control the time distribution required for fuel transportation from the nozzle holes to the flame front, so that the delay time between the heat release rate pulsation and the pressure pulsation is not less than 1 of the oscillation frequency. Within the phase difference range of /4, it eliminates combustion oscillation caused by thermal-acoustic coupling, achieves stable combustion, and plays a suppressive role. And because the nozzle group can ensure the fuel supply under corresponding working conditions, it will not affect the combustion performance.

In one or more embodiments of the fuel nozzle, the fuel orifice extends radially outward from a body of the fuel ring.

In one or more embodiments of the fuel nozzle, each of the nozzle hole groups includes a plurality of fuel nozzle holes evenly distributed along the circumferential direction.

In one or more embodiments of the fuel nozzle, the plurality of coaxial annular shapes are respectively located at a first axial position, a second axial position, a third axial position and a fourth axial position.

In one or more embodiments of the fuel nozzle, the first, second, third, and fourth axial positions are equally spaced in the axial direction.

In one or more embodiments of the fuel nozzle, the axial distance L between the first, second, third, and fourth axial positions satisfies: L/ V=T/8, where V is the movement speed of fuel particles and T is the combustion oscillation period.

In one or more embodiments of the fuel nozzle, the fuel nozzle includes a first state and a second state: in the first state, the fuel nozzle holes of all the nozzle hole groups of the fuel ring in the open state; in the second state, the fuel nozzle holes of part of the nozzle hole groups of the fuel ring are in the closed state, and the remaining nozzle hole groups constitute the combination to form a suppressed oscillation combustion.

In one or more embodiments of the fuel nozzle, the fuel nozzle further includes a first swirler located upstream of the annular chamber and connected to the plurality of fuel injectors. The pores are fluidly connected.

In one or more embodiments of the fuel nozzle, the fuel nozzle includes a main combustion stage and a pre-combustion stage, the main combustion stage includes the annular chamber, and at least part of the pre-combustion stage is covered by the main combustion stage. Surrounded by a combustion stage, the pre-combustion stage includes an annular body having an outer annular portion constituting an annular inner wall of the annular chamber.

In one or more embodiments of the fuel nozzle, the pre-combustion stage includes a pre-combustion stage nozzle located on the axis of the annular body, the annular body also has an inner ring portion, the inner ring portion is provided with a third Two swirlers, the second swirler is in fluid communication with the pre-combustion stage nozzle.

In one or more embodiments of the fuel nozzle, a fuel delivery pipe is further included, and the fuel delivery pipe is connected to one axial end of the annular body of the fuel ring.

According to another aspect of the present invention, a combustion chamber for a gas turbine engine includes: a combustion container; and a fuel nozzle as claimed in any one of claims 1 to 1 located adjacent to the combustion container, the annular shape of the fuel nozzle being The downstream end of the chamber is in direct communication with the combustion vessel and is configured to provide a flow of fuel and air mixture to the combustion vessel.

A gas turbine engine according to yet another aspect of the present invention includes the combustion chamber as described above.

According to yet another aspect of the present invention, a method for suppressing oscillatory combustion in a gas turbine engine includes: providing a main combustion stage, the main combustion stage being configured to pass through a plurality of fuel injection holes located in the main combustion stage Injection into the main combustion stage, wherein the plurality of fuel nozzles at least include nozzle groups with different axial positions, and the nozzle groups are arranged in an annular manner on the annular body to form a group along the annular The body has multiple coaxial annular shapes distributed axially; when oscillatory combustion occurs, the nozzle hole groups are selectively formed into at least one combination, and the nozzle hole groups outside the combination are closed to suppress oscillatory combustion.

According to yet another aspect of the present invention, a fuel ring for a fuel turbine engine includes a ring body and a plurality of fuel injection holes. The plurality of fuel injection holes are distributed along the circumferential direction of the ring body. The plurality of fuel injection holes The injection direction of the nozzle holes is radial; the plurality of fuel nozzle holes at least include nozzle hole groups with different axial positions, and the nozzle hole groups are arranged in the annular body in an annular manner, forming a shape along the A plurality of coaxial rings are axially distributed in the ring body, and the nozzle hole groups can be selectively combined to form at least one combination that suppresses oscillation.

Description of drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description in conjunction with the accompanying drawings and embodiments. In the drawings, the same reference numerals refer to the same features throughout. It should be noted that these The accompanying drawings are only examples, which are not drawn to equal proportions, and should not be used to limit the scope of protection actually claimed by the present invention, wherein:

Figure 1 is a schematic cross-sectional structural diagram of a fuel nozzle according to an embodiment;

Figure 2 is a schematic structural diagram of a fuel nozzle according to an embodiment;

Figure 3 is a schematic structural diagram of the fuel nozzle of an embodiment from another perspective;

Figure 4 is a schematic structural diagram of a fuel ring according to an embodiment;

Figure 5 is a schematic cross-sectional structural diagram of a fuel ring according to an embodiment.

Reference signs:

1000-combustion chamber;

100-Fuel nozzle;

101-main combustion level, 44-main combustion level fuel spray;

102-pre-combustion stage, 41-annular body, 411-outer ring part, 412-inner ring part, 42-pre-combustion stage nozzle, 43-pre-combustion stage fuel spray;

1-Fuel ring, 11-ring body, 1210, 1220, 1230, 1240-coaxial annular shape, 12-fuel nozzle hole, 121, 122, 123, 124-nozzle hole group;

A1-the first axial position, A2-the second axial position, A3-the third axial position, A4-the fourth axial position;

21-annular inner wall, 22-annular outer wall, 201-annular chamber;

301-first cyclone, 302-second cyclone, 3021, 3022-two-stage cyclone;

5-Fuel delivery pipe, 6-Pre-combustion stage fuel delivery pipe;

7-Nozzle housing, 8-Nozzle mounting base.

Detailed ways

Reference will now be made in detail to various embodiments of the invention, examples of which are illustrated in the accompanying drawings and described below. Although the present invention will be described in connection with exemplary embodiments, it should be appreciated that the description is not intended to limit the invention to those exemplary embodiments. On the contrary, the invention is intended to cover not only the exemplary embodiments, but also various alternatives, modifications, equivalents and other forms, which may be included within the spirit and scope of the invention as defined by the appended claims. implementation plan.

In the following description, the orientation or positional relationship indicated by "radial", "axial", "circumferential", "inner", "outer", "upstream", "downstream" or other directional terms is based on the accompanying drawings. The orientation or positional relationship shown is only to facilitate the description of the present invention and simplify the description, and does not indicate or imply that the device or component referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the scope of the present invention. limits. In addition, "upstream" and "downstream" are distinguished based on the direction of fuel flow. Specifically, fuel flows from "upstream" to "downstream"

At the same time, this application uses specific words to describe the embodiments of the application. For example, "one embodiment" and/or "an embodiment" means a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" mentioned twice or more at different places in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics in one or more embodiments of the present application may be appropriately combined.

Currently, with the increasing requirements for low pollution emissions and combustion stability in engine combustion chambers, it is necessary to further improve the performance of the combustion chamber.

After in-depth research, the inventor of this application found that the combustion oscillation phenomenon in the combustion chamber is extremely harmful. The combustion oscillation phenomenon manifests itself as periodic oscillations with large amplitudes in the heat release rate and dynamic pressure generated by fuel combustion in the combustion chamber. When the phase difference between the combustion chamber heat release rate pulsation and the inlet pressure pulsation is less than 1/4 of the oscillation period, a forward coupling occurs between the combustion chamber heat release rate pulsation and the inlet pressure pulsation, resulting in combustion oscillation. For aeroengine combustion chambers using liquid fuel, the delay time between heat release rate pulsation and pressure pulsation is mainly determined by fuel atomization, fuel evaporation, the time required for the combustible mixture to be transported from the nozzle hole to the flame front, and chemical The reaction time is determined by the four factors. Since the time required for fuel atomization, evaporation and chemical reactions is an inherent property of the fuel itself, it is difficult to control.

Based on the above considerations, the inventor conducted in-depth research and in order to regulate the delay time between the heat release rate pulsation and the pressure pulsation and finally decouple the two and suppress the generation of combustion oscillation, the inventor designed a method for gas turbines The fuel nozzle of the engine sets nozzle groups at different axial positions so that the fuel injected from different nozzle groups has different flight times from the injection position to the flame front, thus increasing the relationship between the heat release rate pulsation and the pressure pulsation. The delay time distribution range reduces the probability of in-phase forward coupling of fuel combustion heat release rate pulsation and pressure pulsation in the combustion chamber, reduces the risk of combustion oscillation, and plays a preventive role. At the same time, different nozzle groups can be selectively combined to control the time distribution required for fuel transportation from the nozzle holes to the flame front, so that the delay time between the heat release rate pulsation and the pressure pulsation is not less than 1 of the oscillation frequency. Within the phase difference range of /4, it eliminates combustion oscillation caused by thermal-acoustic coupling, achieves stable combustion, and plays a suppressive role. And because the nozzle group can ensure the fuel supply under corresponding working conditions, it will not affect the combustion performance.

Although the fuel nozzle disclosed in the embodiment of the present application is suitable for use in a gas turbine engine to achieve the effect of suppressing oscillatory combustion, it is not limited to this as long as the engine can use the fuel nozzle disclosed in the embodiment of the present application.

The fuel introduced in the following embodiments takes aviation kerosene as an example, but is not limited to this.

Referring to FIG. 1 and shown in FIG. 2 , in one embodiment, the specific structure of the fuel nozzle 100 for a gas turbine engine may include a fuel ring 1 , an annular inner wall 21 , and an annular outer wall 22 . The fuel ring 1 includes a ring body 11 and a plurality of fuel injection holes 12 . The plurality of fuel injection holes 12 are distributed along the circumferential direction of the ring body 11 . The injection direction of the plurality of fuel injection holes 12 is radial. The annular outer wall 22 surrounds at least part of the annular inner wall 21 to form an annular chamber 201 . Among them, the plurality of fuel injection holes 12 at least include injection hole groups 121, 122, 123, and 124 with different axial positions. The injection hole groups 121, 122, 123, and 124 are arranged in an annular manner on the ring body 11 to form Multiple coaxial rings 1210, 1220, 1230, 1240 and nozzle groups 121, 122, 123, 124 distributed along the axial direction of the ring body 11 can be selectively combined to form at least one combination that suppresses oscillatory combustion.

The "multiple coaxial rings 1210, 1220, 1230, and 1240" here are, for example, as shown in Figures 2 and 3. The rings 1210, 1220, 1230, and 1240 have the same axis a.

The meaning of "the nozzle groups 121, 122, 123, 124 can be selectively combined to form at least one combination that suppresses oscillatory combustion" here specifically means that the nozzle groups can be fully opened or partially opened and partially closed, depending on the actual situation. In the case of oscillating combustion, the combination of nozzle groups is performed. Specific examples are shown in Figures 3 and 4. One combination may be to open the nozzle groups 121 and 124 and close the nozzle groups 122 and 123. The other combination may be to open the nozzle group 122 and close the remaining nozzle groups. , not limited to the above two combination examples, there can also be other types of combinations according to different situations.

Such a beneficial effect is that by arranging nozzle groups with different axial positions, the fuel injected from different nozzle groups has different flight times from the injection position to the flame front, thereby increasing the heat release rate pulsation and pressure pulsation. The delay time distribution range between the combustion chamber fuel combustion heat release rate pulsation and pressure pulsation is reduced, and the probability of in-phase forward coupling is reduced, which reduces the risk of combustion oscillation and plays a preventive role. At the same time, different nozzle groups can be selectively combined and the injection direction of the fuel nozzle holes is radial, which facilitates the control of the time distribution required for fuel transportation from the nozzle holes to the flame front, so that once oscillatory combustion occurs, heat is released. The delay time between rate pulsation and pressure pulsation can be quickly adjusted to not be within the 1/4 phase difference range of the oscillation frequency, eliminating combustion oscillation caused by thermal-acoustic coupling, thereby quickly eliminating the oscillatory combustion phenomenon and achieving stability. Combustion, at the same time, the structure of the fuel ring and nozzle holes makes the combination of the nozzle groups not affect the total fuel supply of the fuel nozzle, only the fuel supply corresponding to each nozzle group changes, which will not affect the combustion performance.

Referring to FIG. 5 , in some embodiments, the specific structure of the fuel injection hole 12 may be that the fuel injection hole 12 extends radially outward from the annular body 11 of the fuel ring 1 . The “annular body 11” here has a hollow structure. The fuel first fills the annular body 11 and then is ejected from the fuel nozzle hole 12. The beneficial effect of this setting is that it facilitates the selective combination control of different nozzle groups, achieves precise control of the delay time between the heat release rate pulsation and the pressure pulsation, and effectively suppresses oscillatory combustion.

Referring to FIGS. 2 to 4 , in some embodiments, the specific structure of the fuel nozzle holes 12 may be such that each nozzle hole group 121 , 122 , 123 , 124 includes a plurality of fuel nozzle holes 12 evenly distributed along the circumferential direction. . The beneficial effect of such an arrangement is that the fuel injected into the annular chamber can be evenly distributed, so that the pressure pulsation and heat release rate pulsation everywhere occur at basically the same time, which facilitates calculation and analysis and selectivity of different nozzle groups. The ground combination suppresses oscillating combustion for control.

In some embodiments, as shown in FIGS. 2 to 5 , the circumferential positions of adjacent fuel nozzle holes 12 are alternately distributed, so that the fuel in each nozzle hole group can be evenly distributed and ensure the uniformity of combustion.

Referring to FIG. 3 , in some embodiments, the specific structure of the fuel injection hole 12 may be that a plurality of coaxial annular shapes 1210 , 1220 , 1230 , and 1240 are respectively located at the first axial position A1 , the second axial position A2 , The third axial position A3 and the fourth axial position A4. That is, the coaxial rings have the same axial position as a whole, which makes it easy to design and process the fuel ring, and it is also easy to simulate, calculate and calibrate different combinations of different nozzle groups.

Continuing to refer to FIG. 3 , in some embodiments, the specific structure of the fuel injection hole 12 may be a first axial position A1 , a second axial position A2 , a third axial position A3 , and a fourth axial position A4 distributed equally in the axial direction. The beneficial effect of this setting is that the equally spaced distribution makes the flight time of the fuel injected from different nozzle groups from the injection position to the flame front an integral multiple relationship, which facilitates calculation and analysis, and accurately controls the selective control of different nozzle groups. Combination to improve the effect of suppressing oscillatory combustion.

Continuing to refer to FIG. 3 , in some embodiments, the specific structure of the fuel injection hole 12 may be a first axial position A1 , a second axial position A2 , a third axial position A3 , and a fourth axial position A4 The distance L in the axial direction satisfies: L/V=T/8, where V is the movement speed of the fuel particles and T is the combustion oscillation period.

The "combustion oscillation period T" here is determined based on the frequency of combustion oscillation. Assuming that the frequency of combustion oscillation is f, the corresponding combustion oscillation period T is T=1/f.

The principle of "the axial spacing L satisfies: L/V=T/8" here is to control the difference in flight time of the fuel injected from adjacent fuel nozzle holes to reach the flame surface to be 1/8 of the combustion oscillation period.

The beneficial effect of this setting is that the delay time between the heat release rate pulsation and the pressure pulsation can be located outside the 1/4 oscillation period, preventing the forward coupling of the heat release rate pulsation and the pressure pulsation, and reducing the frequency of combustion oscillation. Eliminate combustion oscillations when oscillatory combustion occurs and ensure stable combustion.

Referring to FIGS. 1 to 5 , in some embodiments, the specific structure of the fuel nozzle 100 may be that the fuel nozzle 100 includes a first state and a second state:

In the first state, the fuel nozzle holes 12 of all the nozzle hole groups 121, 122, 123, and 124 of the fuel ring 1 are in an open state. At this time, combustion is in a stable state.

In the second state, some of the fuel nozzle holes 12 of the nozzle groups 121, 122, 123, and 124 of the fuel ring 1 are in a closed state, and the remaining nozzle groups 121, 122, 123, and 124 form a combination to form a suppressed oscillation combustion. . At this time, combustion is in an oscillating state.

The principle is that when combustion oscillation occurs, the phase difference between the heat release rate pulsation and the pressure pulsation generated by fuel combustion is obtained through calculation analysis or experimental measurement. At this time, only the nozzle group at a specific axial position is selected to inject material to adjust the heat. The phase relationship between the release rate pulsation and the pressure pulsation, that is, the size of the delay time, makes the delay time lie outside 1/4 of the oscillation period, so that the heat release rate pulsation and the pressure pulsation do not undergo forward coupling, eliminating oscillatory combustion and making combustion Stability is restored.

In some embodiments, nozzle groups at different axial positions are controlled by different valve switches, so that the nozzle group at a specific axial position can be freely and flexibly selected to inject fuel under different oscillatory combustion situations, thereby ensuring that the fuel reaches the flame. The flight time of the front is regulated to obtain the required delay time between heat release rate pulsation and pressure pulsation, eliminate the forward coupling of heat release rate pulsation and pressure pulsation, suppress oscillatory combustion, and restore combustion to a stable state.

Referring to FIG. 1 , in some embodiments, the fuel nozzle 100 further includes a first swirler 301 located upstream of the annular chamber 201 and in fluid communication with the plurality of fuel injection holes 12 . With such a simple arrangement, the fuel injected from the fuel nozzle hole and the incoming flow passing through the first swirler can be premixed to form a fuel spray for combustion.

In some embodiments, as shown in FIG. 1 , the normal direction b of the fuel nozzle hole 12 is perpendicular to the incoming flow direction c entering through the first swirler 301 , so that the fuel injected from the fuel nozzle hole 12 is in line with the high-speed incoming flow. Perform transverse shearing to obtain excellent fuel atomization and blending properties, promote full combustion, and reduce pollutant emissions. The "vertical" here does not need to be a strict 90-degree angle, it only needs to make the fuel and the high-speed incoming flow undergo transverse shear.

Continuing to refer to FIG. 1 , in some embodiments, the specific structure of the fuel nozzle 100 may include a main combustion stage 101 and a pre-combustion stage 102 . The main combustion stage 101 includes an annular chamber 201 , and at least part of the pre-combustion stage 102 Surrounded by the main combustion stage 101 , the pre-combustion stage 102 includes an annular body 41 having an outer annular portion 411 constituting the annular inner wall 21 of the annular chamber 201 .

Continuing to refer to FIG. 1 , in some embodiments, the specific structure of the precombustion stage 102 may be that the precombustion stage 102 includes a precombustion stage nozzle 42 located on the axis of the annular body 41 , and the annular body 41 also has an inner annular portion 412 , the inner ring portion 412 is provided with a second swirler 302, and the second swirler 302 is in fluid communication with the pre-combustion stage nozzle 42. The fuel is sprayed through the pre-combustion stage nozzle 42 to form a pre-combustion stage fuel spray 43, and then mixed with the incoming flow entering through the second swirler 302 to form a combustible mixture. In some embodiments, as shown in FIG. 1 , the second swirler 302 includes two-stage swirlers 3021 and 3022 to increase the incoming flow rate so that the pre-combustion stage fuel spray 43 can be fully burned. The ring body 11 of the fuel ring 1 is located in the radial space between the inner ring portion 412 and the outer ring portion 411 . The structure of the outer ring part 411 and the inner ring part 412 can be a single ring body or multiple ring bodies. For example, the outer ring part 411 shown in the figure has a single ring body structure, and the inner ring part 412 has a plurality of ring bodies. The structure of the ring.

The main combustion stage and pre-combustion stage are set up in this way to form staged combustion. The main combustion stage uses premixed combustion and the pre-combustion stage uses diffusion combustion, which can effectively reduce engine pollution emissions. The advantage of premixed combustion in the main combustion stage is that it can reduce the flame combustion temperature, thereby reducing NOx emissions in the combustion chamber; the disadvantage is that the premixed fuel-air mixture is easily disturbed by the air flow pressure, causing a coupling between pressure pulsation and heat release rate pulsation. , resulting in combustion oscillation. Arranging the annular chamber including the above-mentioned fuel ring in the main combustion stage can effectively prevent and suppress oscillating combustion, stabilize combustion, and improve safety.

Continuing to refer to FIG. 1 , in some embodiments, the specific structure of the fuel nozzle 100 may further include a fuel delivery pipe 5 , and the fuel delivery pipe 5 is connected to one axial end of the ring body 11 of the fuel ring 1 . The fuel enters the ring body 11 through the fuel delivery pipe 5, and is then transported to each fuel nozzle hole 12 through the ring body 11. The number of fuel nozzle holes 12 is generally a multiple of the number of groups of nozzle holes. For example, the implementation shown in the figure For example, there are four groups of nozzle holes 121, 122, 123, and 124. Each group of nozzle holes has the same number of nozzle holes. There are 12 to 24 fuel nozzle holes in total. This makes it easy to process the fuel ring and the fuel nozzle. Corresponding simulation calculation and calibration.

In some embodiments, as shown in FIG. 1 , the fuel nozzle 100 further includes a pre-combustion stage fuel delivery pipe 6 connected to one axial end of the pre-combustion stage nozzle 42 .

In some embodiments, as shown in FIG. 1 , the fuel nozzle 100 further includes a nozzle housing 7 and a nozzle mounting seat 8 . One side of the nozzle housing 7 is connected to the annular outer wall 22 through the first swirler 301 , and the other side is connected to the nozzle. The mounting seat 8 is connected, and the other ends of the fuel delivery pipe 5 and the pre-combustion stage fuel delivery pipe 6 are connected to the outer pipeline of the fuel nozzle 100 through the nozzle mounting seat 8 to deliver fuel.

Continuing to refer to FIG. 1 , in one embodiment, the specific structure of the combustion chamber 1000 for a gas turbine engine may include a combustion vessel (not shown in the figure) and a structure as described above disposed adjacent to the combustion vessel. Fuel nozzle 100. The downstream end of the annular chamber 201 of the fuel nozzle 100 is directly connected to the combustion vessel and is configured to provide a flow of fuel and air mixture to the combustion vessel. Specifically, as shown in Figure 1, the pre-combustion stage fuel enters the pre-combustion stage nozzle 42 through the pre-combustion stage fuel delivery pipe 6 and is sprayed out, forming a pre-combustion stage fuel spray 43. The pre-combustion stage air passes through the two-stage swirler and is mixed with the pre-combustion stage air. The pre-combustion stage fuel spray 43 interacts with each other to form a combustible mixed gas, thereby realizing the supply and full atomization and mixing of the pre-combustion stage fuel, and spraying it to the combustion container. The main combustion stage fuel enters the ring body 11 through the fuel delivery pipe 5, and then the fuel is delivered to the fuel nozzle hole 12 through the ring body 11, and is sprayed out through the fuel nozzle hole 12. The main combustion stage air passes through the first swirler 301 to generate swirl. flow, and performs high-speed shearing with the fuel injected normal to direction b through the fuel nozzle hole 12 to achieve atomization of the main combustion stage fuel, forming a main combustion stage fuel spray 44, which is sprayed to the combustion container.

The beneficial effect of this arrangement is that the combustion chamber using the above-mentioned fuel nozzle 100 can prevent and eliminate combustion oscillations and improve the combustion stability of the combustion chamber.

In one embodiment, a gas turbine engine may be configured to include a combustion chamber 1000 as described above. Using the combustion chamber as described above can effectively suppress oscillatory combustion, ensure stable operation of the engine, and improve engine safety.

Referring to FIGS. 1 to 5 , in one embodiment, specific steps of a method for suppressing oscillatory combustion for a gas turbine engine may include: providing a main combustion stage 101 , and the main combustion stage 101 is set to: A plurality of fuel injection holes 12 of the main combustion stage 101 are injected into the main combustion stage 101, wherein the plurality of fuel injection holes 12 at least include injection hole groups 121, 122, 123, 124 with different axial positions. The injection hole groups 121, 122, 123, 124 are arranged on the ring body 11 in an annular arrangement, forming a plurality of coaxial rings 1210, 1220, 1230, 1240 distributed along the axial direction of the ring body 11; when oscillatory combustion occurs, the nozzle group is At least one combination is selectively formed, and nozzle groups outside the combination are closed to suppress oscillatory combustion. The specific principle is that since the nozzle groups 121, 122, 123, and 124 have different axial positions, when combustion oscillation occurs in the combustion chamber, the relationship between the heat release rate pulsation and the pressure pulsation generated by fuel combustion can be obtained through calculation analysis or experimental measurement. Phase difference, at this time, choose to open only a specific nozzle group to inject material, and adjust the phase relationship between the heat release rate pulsation and pressure pulsation of the combustion chamber, that is, the delay time of the two, so that the delay time of the two is located at 1/4 oscillation Outside the cycle, the flight time of most fuel nozzles under any operating condition of the engine is not within the 1/4 phase difference range of the oscillation frequency, eliminating the combustion oscillation caused by thermal-acoustic forward coupling, achieving stable combustion, and simultaneously The setting of each fuel injection hole does not affect the combustion performance under this working condition, ensuring the normal operation of the engine.

Based on the above introduction, those skilled in the art can understand that the fuel ring used in the fuel turbine engine can be sold as an accessory of the engine together with the entire engine, or it can be sold as a separate product. Manufacturing and selling, therefore, fuel rings for use in fuel turbine engines also fall within the scope of the present invention. Referring to FIGS. 2 to 5 , in one embodiment, the specific structure of the fuel ring 1 for a fuel turbine engine may include a ring body 11 and a plurality of fuel nozzle holes 12 along the ring. The circumferential distribution of the body 11, the injection direction of the plurality of fuel injection holes 12 is radial; the plurality of fuel injection holes 12 at least include injection hole groups 121, 122, 123, 124 with different axial positions, the injection hole groups 121, 122, 123, 124 are arranged on the ring body 11 in an annular arrangement, forming a plurality of coaxial rings 1210, 1220, 1230, 1240 distributed along the axial direction of the ring body 11, and the nozzle hole groups 121, 122, 123, 124 Can be selectively combined to form at least one combination that suppresses oscillation. The fuel ring of this embodiment can be used to regulate the delay time for the fuel to reach the flame front and participate in combustion after it is ejected from the fuel nozzle hole, so that the flight time of most of the fuel nozzle holes is not in the thermal-acoustic phase under any operating conditions of the engine. Within the coupling phase difference range, the thermal-acoustic coupling intensity is weakened, the combustion stability of the engine combustion chamber is enhanced, the engine is guaranteed to operate stably, and the engine safety is improved.

In summary, the beneficial effects of the gas turbine engine and the fuel nozzle, combustion chamber, fuel ring and method for suppressing oscillation combustion introduced in the above embodiments include but are not limited to one or a combination of the following:

1. The fuel nozzle sets nozzle groups with different axial positions, so that the fuel injected from different nozzle groups has different flight times from the injection position to the flame front, thereby increasing the difference between the heat release rate pulsation and the pressure pulsation. The delay time distribution range reduces the probability of in-phase forward coupling of fuel combustion heat release rate pulsation and pressure pulsation in the combustion chamber, reduces the risk of combustion oscillation, and plays a preventive role. At the same time, different nozzle groups can be selectively combined to control the time distribution required for fuel transportation from the nozzle holes to the flame front, so that the delay time between the heat release rate pulsation and the pressure pulsation is not less than 1 of the oscillation frequency. Within the phase difference range of /4, it eliminates combustion oscillation caused by thermal-acoustic coupling, achieves stable combustion, and plays a suppressive role. And because the nozzle group can ensure the fuel supply under corresponding working conditions, it will not affect the combustion performance.

2. The combustion chamber using the above fuel nozzle can prevent and eliminate combustion oscillations and improve the combustion stability of the combustion chamber.

3. A gas turbine engine using a combustion chamber as described above can effectively suppress oscillatory combustion, ensure stable operation of the engine, and improve engine safety.

4. Using the method for suppressing oscillatory combustion in gas turbine engines, the delay time of heat release rate pulsation and pressure pulsation can be controlled, thereby eliminating combustion oscillations caused by thermal-acoustic forward coupling, achieving stable combustion, and simultaneously multiple The setting of the fuel injection holes does not affect the combustion performance under this working condition, ensuring the normal operation of the engine.

5. The fuel ring of the present application can be used to regulate the delay time for the fuel to reach the flame front and participate in combustion after it is ejected from the fuel nozzle hole, so that the flight time of most of the fuel nozzle holes is not in the thermal-acoustic state under any operating conditions of the engine. Within the phase coupling phase difference range, the thermal-acoustic coupling intensity is weakened, the combustion stability of the engine combustion chamber is enhanced, the engine is guaranteed to operate stably, and the engine safety is improved.

Although the present invention is disclosed above in terms of preferred embodiments, they are not intended to limit the invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims (15)

1. A fuel nozzle (100) for a gas turbine engine, comprising:

the fuel ring (1) comprises a ring body (11) and a plurality of fuel spray holes (12), wherein the plurality of fuel spray holes (12) are distributed along the circumferential direction of the ring body (11), and the injection direction of the plurality of fuel spray holes (12) is radial;

an annular inner wall (21);

-an annular outer wall (22) forming an annular chamber (201) around at least part of said annular inner wall (21);

wherein the plurality of fuel injection holes (12) at least comprises injection hole groups (121, 122, 123, 124) with different axial positions, the injection hole groups (121, 122, 123, 124) are arranged on the ring body (11) in a ring arrangement manner to form a plurality of coaxial rings (1210, 1220, 1230, 1240) distributed along the axial direction of the ring body (11), and the injection hole groups (121, 122, 123, 124) can be selectively combined to form at least one combination for suppressing oscillation combustion.

2. The fuel nozzle (100) of claim 1, wherein the fuel orifice (12) extends radially outwardly from the annulus (11) of the fuel ring (1).

3. The fuel nozzle (100) of claim 1, wherein each of the nozzle hole groups (121, 122, 123, 124) includes a plurality of fuel nozzle holes (12) that are uniformly distributed in a circumferential direction.

4. A fuel nozzle (100) according to any one of claims 1-3, wherein the plurality of coaxial rings (1210, 1220, 1230, 1240) are located at a first axial position (A1), a second axial position (A2), a third axial position (A3) and a fourth axial position (A4), respectively.

5. The fuel nozzle (100) of claim 4, wherein the first axial position (A1), the second axial position (A2), the third axial position (A3), and the fourth axial position (A4) are equally spaced axially.

6. The fuel nozzle (100) of claim 5, wherein the first axial position (A1), the second axial position (A2), the third axial position (A3), the fourth axial position (A4) have an axial spacing L that satisfies: l/v=t/8, where V is the fuel particle movement velocity and T is the combustion oscillation period.

7. The fuel nozzle (100) of claim 1, wherein the fuel nozzle (100) comprises a first state and a second state:

in the first state, all fuel injection holes (12) of the injection hole groups (121, 122, 123, 124) of the fuel ring (1) are in an open state;

in the second state, part of the groups of fuel orifices (121, 122, 123, 124) of the fuel ring (1) are in a closed state with the remaining groups of orifices (121, 122, 123, 124) constituting the combination to form a combustion-suppressing oscillation.

8. The fuel nozzle (100) of claim 1, wherein the fuel nozzle (100) further comprises a first swirler (301), the first swirler (301) being located upstream of the annular chamber (201) in fluid communication with the plurality of fuel injection holes (12).

9. The fuel nozzle (100) of claim 1, wherein the fuel nozzle (100) comprises a main combustion stage (101) and a pre-combustion stage (102), the main combustion stage (101) comprising the annular chamber (201), at least part of the pre-combustion stage (102) being surrounded by the main combustion stage (101), the pre-combustion stage (102) comprising an annular body (41), the annular body (41) having an outer annular portion (411), the outer annular portion (411) constituting an annular inner wall (21) of the annular chamber (201).

10. The fuel nozzle (100) of claim 9, wherein the pre-stage (102) comprises a pre-stage nozzle (42) located at an axis of an annular body (41), the annular body (41) further having an inner annulus (412), the inner annulus (412) being provided with a second swirler (302), the second swirler (302) being in fluid communication with the pre-stage nozzle (42).

11. The fuel nozzle (100) of claim 1, further comprising a fuel delivery tube (5), the fuel delivery tube (5) connecting an axial end of the annulus (11) of the fuel ring (1).

12. A combustor (1000) for a gas turbine engine, comprising:

a combustion vessel; and

the fuel nozzle (100) of any of claims 1-11 disposed adjacent to the combustion vessel, a downstream end of an annular chamber (201) of the fuel nozzle (100) being in direct communication with the combustion vessel, configured to provide a flow of a fuel and air mixture to the combustion vessel.

13. A gas turbine engine, comprising a combustion chamber (1000) according to claim 12.

14. A method for suppressing oscillating combustion for a gas turbine engine, comprising:

-providing a main combustion stage (101), the main combustion stage (101) being arranged to:

injecting into the main combustion stage (101) through a plurality of fuel injection holes (12) located in the main combustion stage (101), wherein the plurality of fuel injection holes (12) at least comprise injection hole groups (121, 122, 123, 124) with different axial positions, the injection hole groups (121, 122, 123, 124) are arranged in an annular arrangement on a ring body (11) to form a plurality of coaxial rings (1210, 1220, 1230, 1240) distributed along the axial direction of the ring body (11); when the oscillating combustion occurs, the nozzle hole group is selectively formed into at least one combination, and the nozzle hole group other than the combination is closed to suppress the oscillating combustion.

15. A fuel ring (1) for a fuel turbine engine, comprising a ring body (11) and a plurality of fuel injection holes (12), the plurality of fuel injection holes (12) being distributed along the circumference of the ring body (11), the injection direction of the plurality of fuel injection holes (12) being radial; the plurality of fuel injection holes (12) at least comprises injection hole groups (121, 122, 123, 124) with different axial positions, the injection hole groups (121, 122, 123, 124) are arranged on the ring body (11) in a ring arrangement mode to form a plurality of coaxial rings (1210, 1220, 1230, 1240) distributed along the axial direction of the ring body (11), and the injection hole groups (121, 122, 123, 124) can be selectively combined to form at least one combination for suppressing oscillation.