CN116734289A - Gas turbine engine and fuel nozzle, combustor, fuel ring and oscillation-suppressing combustion method therefor - Google Patents

Abstract

The application provides a gas turbine engine, a fuel nozzle, a combustion chamber, a fuel ring and a method for suppressing oscillation combustion for the gas turbine engine. Wherein the fuel nozzle comprises: the fuel ring comprises a ring body and a plurality of fuel spray holes, the plurality of fuel spray holes are distributed along the circumferential direction of the ring body, and the injection direction of the plurality of fuel spray holes is radial; an annular inner wall; an annular outer wall forming an annular chamber around at least a portion of the annular inner wall; the fuel injection holes at least comprise injection hole groups with different axial positions, the injection hole groups are arranged on the ring body in a ring arrangement mode to form a plurality of coaxial rings distributed along the axial direction of the ring body, and the injection hole groups can be selectively combined to form at least one combination for suppressing oscillation combustion. The suppression of the oscillating combustion is realized.

Description

Gas turbine engine and fuel nozzle, combustor, fuel ring and oscillation-suppressing combustion method therefor

Technical Field

The present application relates to the field of aeroengines, in particular to gas turbine engines, fuel nozzles, combustors, fuel rings and methods of suppressing oscillating combustion therefor.

Background

The combustion chamber of the modern low-pollution lean-burn engine is extremely easy to generate combustion oscillation phenomenon, the combustion oscillation phenomenon affects the safe and stable operation of the gas turbine and the aeroengine, the oscillation can further lead to the vibration of the engine structure, the rise of the rotation speed and the load of the engine is limited, flameout and backfire are induced, and serious consequences such as failure and explosion of engine parts are caused. In addition, in the development process of the aero-engine and the gas turbine, the development process of parts and the whole machine is often influenced due to the thermoacoustic oscillation phenomenon, and the development progress of the project is delayed.

Disclosure of Invention

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

It is a further object of the present application to provide a combustor for a gas turbine engine.

It is a further object of the present application to provide a gas turbine engine.

It is a further object of the present application to provide a method for suppressing oscillating combustion for a gas turbine engine.

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

A fuel nozzle for a gas turbine engine according to one aspect of the application includes: the fuel ring comprises a ring body and a plurality of fuel spray holes, wherein the plurality of fuel spray holes are distributed along the circumferential direction of the ring body, and the spray direction of the plurality of fuel spray holes is radial; an annular inner wall; an annular outer wall forming an annular chamber around at least a portion of the annular inner wall; the fuel injection holes at least comprise injection hole groups with different axial positions, the injection hole groups are arranged on the ring body in an annular arrangement mode to form a plurality of coaxial annular shapes distributed along the axial direction of the ring body, and the injection hole groups can be selectively combined to form at least one combination for suppressing oscillation combustion.

According to the technical scheme, through the arrangement of the spray hole groups at different axial positions, fuel sprayed from the spray hole groups has different flight times from the spray position to the flame frontal surface, so that the delay time distribution range between the heat release rate pulsation and the pressure pulsation is enlarged, the probability of occurrence of same-phase positive coupling of the combustion heat release rate pulsation and the pressure pulsation of fuel combustion in the combustion chamber is reduced, the risk of occurrence of combustion oscillation is reduced, and a preventive effect is achieved. Meanwhile, different jet orifice groups can be selectively combined, so that the time distribution required by transporting fuel from the jet orifice to the flame front is regulated and controlled, the delay time between the heat release rate pulsation and the pressure pulsation is not in the 1/4 phase difference range of the oscillation frequency, the combustion oscillation caused by the heat-sound coupling is eliminated, the stable combustion is realized, and the inhibition effect is realized. And the fuel supply quantity under the corresponding working condition can be ensured by arranging the spray hole group, so that the combustion performance is not influenced.

In one or more embodiments of the fuel nozzle, the fuel orifices extend radially outward from a annulus 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 that are uniformly distributed in a circumferential direction.

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

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

In one or more embodiments of the fuel nozzle, the first, second, third, and fourth axial positions are axially spaced apart by a distance L that satisfies: l/v=t/8, where V is the fuel particle movement velocity 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, all fuel spray holes of the spray hole groups of the fuel ring are in an open state; in the second state, a part of fuel spray holes of the spray hole group of the fuel ring are in a closed state, and the rest spray hole groups form the combination so as to form the vibration combustion suppression.

In one or more embodiments of the fuel nozzle, the fuel nozzle further includes a first swirler upstream of the annular chamber in fluid communication with the plurality of fuel orifices.

In one or more embodiments of the fuel nozzle, the fuel nozzle includes a main combustion stage including the annular chamber and a pre-combustion stage, at least a portion of the pre-combustion stage being surrounded by the main combustion stage, the pre-combustion stage including an annular body having an outer annular portion that forms an annular inner wall of the annular chamber.

In one or more embodiments of the fuel nozzle, the pre-stage includes a pre-stage nozzle located at an axis of an annular body, the annular body further having an inner ring portion provided with a second swirler in fluid communication with the pre-stage nozzle.

In one or more embodiments of the fuel nozzle, a fuel delivery tube is further included, the fuel delivery tube connecting an axial end of the annulus of the fuel ring.

According to another aspect of the application, a combustor for a gas turbine engine includes: a combustion vessel; the fuel nozzle of any of claims disposed adjacent to the combustion vessel, a downstream end of the annular chamber of the fuel nozzle being in direct communication with the combustion vessel and configured to provide a flow of a fuel and air mixture to the combustion vessel.

A gas turbine engine according to yet another aspect of the application comprises a combustion chamber as described above.

A method for suppressing oscillating combustion for a gas turbine engine according to yet another aspect of the application includes: providing a main combustion stage, the main combustion stage being arranged to: injecting a plurality of fuel spray holes positioned in the main combustion stage into the main combustion stage, wherein the plurality of fuel spray holes at least comprise spray hole groups with different axial positions, and the spray hole groups are arranged on a ring body in an annular arrangement manner to form a plurality of coaxial rings distributed along the axial direction of the ring body; 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.

A fuel ring for a fuel turbine engine according to still another aspect of the present application includes a ring body and a plurality of fuel injection holes distributed along a circumferential direction of the ring body, an injection direction of the plurality of fuel injection holes being radial; the plurality of fuel injection holes at least comprise injection hole groups with different axial positions, the injection hole groups are arranged on the ring body in an annular arrangement mode to form a plurality of coaxial rings distributed along the axial direction of the ring body, and the injection hole groups can be selectively combined to form at least one combination for suppressing oscillation.

Drawings

The above and other features, properties and advantages of the present application will become more apparent from the following description of the accompanying drawings and embodiments in which like reference numerals refer to like features throughout, it being noted that these drawings are given by way of example only, which are not drawn to scale and should not be construed to limit the true scope of the application, wherein:

FIG. 1 is a schematic cross-sectional view of a fuel nozzle of an embodiment;

FIG. 2 is a schematic illustration of a fuel nozzle of an embodiment;

FIG. 3 is a schematic structural view of another view of a fuel nozzle of an embodiment;

FIG. 4 is a schematic illustration of the structure of a fuel ring according to an embodiment;

FIG. 5 is a schematic cross-sectional view of a fuel ring according to an embodiment.

Reference numerals:

1000-combustion chamber;

100-fuel nozzles;

101-main stage, 44-main stage fuel spray;

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

1-fuel ring, 11-ring, 1210, 1220, 1230, 1240-coaxial ring, 12-fuel nozzle, 121, 122, 123, 124-nozzle group;

a1-a first axial position, A2-a second axial position, A3-a third axial position, A4-a fourth axial position;

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

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

5-fuel delivery pipe, 6-pre-combustion grade fuel delivery pipe;

7-nozzle housing, 8-nozzle mount.

Detailed Description

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

In the description that follows, references to orientations or positional relationships that are indicated by "radial," "axial," "circumferential," "inner," "outer," "upstream," "downstream," or other azimuthal terms are based on the orientation or positional relationships shown in the drawings, are merely for convenience in describing the application and simplifying the description, and do not indicate or imply that the devices or components referred to must have a particular orientation, be configured and operated in a particular orientation, and therefore should not be construed as limiting the application. In addition, "upstream" and "downstream" are distinguished based on the direction of fuel flow, specifically, the fuel flows from "upstream" to "downstream"

Meanwhile, the present application uses specific words to describe embodiments of the present application. Reference to "one embodiment" and/or "an embodiment" means that a particular feature, structure, or characteristic is associated with at least one embodiment of the application. Thus, it should be emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" in various positions in this specification are not necessarily referring to the same embodiment. Furthermore, certain features, structures, or characteristics of one or more embodiments of the application may be combined as suitable.

At present, with increasing demands for low pollution emissions and combustion stability of engine combustors, further improvements in the performance of combustors are required.

Through intensive research, the inventor of the application discovers that the combustion oscillation phenomenon of the combustion chamber is huge in hazard, and the combustion oscillation phenomenon is represented by periodic oscillation with large amplitude of 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 smaller than 1/4 oscillation period, positive coupling is generated between the combustion chamber heat release rate pulsation and the inlet pressure pulsation, resulting in combustion oscillation. For an aircraft engine combustion chamber using liquid fuel, the delay time between the heat release rate pulsation and the pressure pulsation is mainly determined by the four components of fuel atomization, fuel evaporation, the time required for the combustible blend to be transported from the injection orifice to the flame front, and the time required for the chemical reaction. Since the time required for fuel atomization, evaporation and chemical reaction is inherent to the fuel itself, it is difficult to regulate.

Based on the above considerations, the inventor has conducted intensive studies, in order to regulate and control the delay time between the heat release rate pulsation and the pressure pulsation and finally decouple the heat release rate pulsation and the pressure pulsation, and inhibit the generation of combustion oscillation, the inventor has devised a fuel nozzle for a gas turbine engine, and by arranging nozzle hole groups at different axial positions, the fuels injected from the nozzle hole groups have different flight times from the injection positions to the flame front, thereby increasing the delay time distribution range between the heat release rate pulsation and the pressure pulsation, reducing the probability of occurrence of same-phase forward coupling of the heat release rate pulsation and the pressure pulsation of fuel combustion in a combustion chamber, reducing the risk of occurrence of combustion oscillation, and playing a role in prevention. Meanwhile, different jet orifice groups can be selectively combined, so that the time distribution required by transporting fuel from the jet orifice to the flame front is regulated and controlled, the delay time between the heat release rate pulsation and the pressure pulsation is not in the 1/4 phase difference range of the oscillation frequency, the combustion oscillation caused by the heat-sound coupling is eliminated, the stable combustion is realized, and the inhibition effect is realized. And the fuel supply quantity under the corresponding working condition can be ensured by arranging the spray hole group, so that the combustion performance is not influenced.

Although the fuel nozzle disclosed in the embodiment of the present application is suitable for a gas turbine engine to achieve the effect of suppressing the oscillating combustion, the fuel nozzle is not limited thereto, and any fuel nozzle disclosed in the embodiment of the present application may be used as long as the engine can be used.

The fuel described in the following examples is exemplified by aviation kerosene, but is not limited thereto.

Referring to FIG. 1 in conjunction with FIG. 2, in one embodiment, a particular configuration of a 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, and the injection direction of the plurality of fuel injection holes 12 is radial. The annular outer wall 22 forms an annular chamber 201 around at least part of the annular inner wall 21. Wherein the plurality of fuel injection holes 12 at least comprise injection hole groups 121, 122, 123, 124 having different axial positions, the injection hole groups 121, 122, 123, 124 are disposed on the ring body 11 in an annular arrangement to form a plurality of coaxial annular shapes 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 the oscillating combustion.

The "plurality of coaxial rings 1210, 1220, 1230, 1240" herein, such as shown in fig. 2, 3, have the same axis a as the rings 1210, 1220, 1230, 1240.

The meaning of "the nozzle hole groups 121, 122, 123, 124 may be selectively combined to form at least one combination that suppresses the oscillating combustion" herein means specifically that the nozzle hole groups may be fully opened or partially opened and partially closed, and the combination of the nozzle hole groups is performed according to the actual oscillating combustion. For example, as shown in fig. 3 and fig. 4, one of the combinations may be an open nozzle group 121 and 124, and a close nozzle group 122 and 123, and the other combination may be an open nozzle group 122 and a close nozzle group, which is not limited to the above two examples, and other combinations may be available according to different situations.

The beneficial effects of this are that through setting up the orifice group of different axial positions for the fuel that sprays from different orifice groups has different flight time from injection position to flame frontal, and then increases the delay time distribution scope between heat release rate pulsation and the pressure pulsation, reduces the combustion chamber fuel burning heat release rate pulsation and the same phase forward coupling probability of pressure pulsation, reduces the risk that the burning vibration takes place, plays the prevention effect. Meanwhile, different jet hole groups can be selectively combined, the jet direction of the fuel jet holes is radial, the time distribution required by the fuel to be transported from the jet holes to the flame front is convenient to adjust, once oscillation combustion occurs, the delay time between the heat release rate pulsation and the pressure pulsation can be quickly adjusted to be not in the 1/4 phase difference range of the oscillation frequency, combustion oscillation caused by heat-sound coupling is eliminated, so that the oscillation combustion phenomenon is quickly eliminated, stable combustion is realized, meanwhile, the fuel ring and the jet hole structure enable the combination of the jet hole groups not to influence the total fuel supply quantity of the fuel jet nozzle, and only the fuel supply quantity corresponding to each jet hole group is changed, so that the combustion performance is not influenced.

Referring to FIG. 5, in some embodiments, the specific configuration of the fuel injection holes 12 may be such that the fuel injection holes 12 extend radially outward from the annulus 11 of the fuel ring 1. The ring body 11 is hollow, and fuel is filled in the ring body 11 and then sprayed out from the fuel spray holes 12. The beneficial effect that so set up lies in, is convenient for selectively make up the control to different orifice groups, realizes the accurate regulation and control to the delay time between heat release rate pulsation and the pressure pulsation, effectively plays the effect of suppressing the oscillation combustion.

Referring to fig. 2-4, in some embodiments, the specific configuration of the fuel injection holes 12 may be such that each injection hole group 121, 122, 123, 124 includes a plurality of fuel injection holes 12 that are uniformly distributed in the circumferential direction. The beneficial effect of this arrangement lies in that can make the fuel that sprays into in the annular chamber evenly distributed, and then make the time that pressure pulsation and the heat release rate pulsation of everywhere produced respectively basically the same, be convenient for calculate analysis and control the vibration combustion that suppresses of selectively combining of different orifice groups.

In some embodiments, as shown in fig. 2-5, the circumferential positions of adjacent fuel injection holes 12 are alternately distributed, so that the fuel of each injection hole group can be uniformly distributed, and the uniformity of combustion is ensured.

Referring to FIG. 3, in some embodiments, the fuel injection orifice 12 may be specifically configured with a plurality of coaxial rings 1210, 1220, 1230, 1240 positioned at a first axial position A1, a second axial position A2, a third axial position A3, and a fourth axial position A4, respectively. The coaxial rings are all in the same axial position, so that the design and the processing of the fuel ring are easy, and the simulation calculation and the calibration of different combinations of different spray hole groups are easy.

With continued reference to FIG. 3, in some embodiments, the specific configuration of the fuel injection orifices 12 may be such that the first, second, third, and fourth axial positions A1, A2, A3, A4 are equally spaced axially. The beneficial effects of the arrangement are that the equidistant distribution ensures that the flight time from the injection position to the flame frontal surface of the fuel injected from different jet orifice groups is in an integral multiple relation, thereby facilitating calculation and analysis, accurately controlling the selective combination of different jet orifice groups and improving the effect of suppressing oscillation combustion.

With continued reference to FIG. 3, in some embodiments, the specific configuration of the fuel injection orifices 12 may be such that the first, second, third, and fourth axial positions A1, A2, A3, 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.

Here, the "combustion oscillation period T" is determined based on the combustion oscillation occurrence frequency, and assuming that the combustion oscillation occurrence frequency is f, the corresponding combustion oscillation period T is t=1/f.

The "axial spacing L" here satisfies: the principle of L/v=t/8 "is to control the time-of-flight difference of fuel injected from adjacent fuel injection holes to the flame face to be 1/8 combustion oscillation period.

The beneficial effect of this arrangement lies in, can make the delay time between heat release rate pulsation and the pressure pulsation lie in 1/4 oscillation period outside, prevents that heat release rate pulsation and pressure pulsation from taking place forward coupling, reduces the frequency of occurrence of burning oscillation, eliminates the condition of burning oscillation when the oscillation combustion takes place, guarantees stable burning.

Referring to fig. 1-5, in some embodiments, a specific configuration 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 injection holes 12 of the injection hole groups 121, 122, 123, 124 of all the fuel rings 1 are in an open state. At this time, the combustion is in a steady state.

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

The principle is that after combustion oscillation occurs, the phase difference between heat release rate pulsation and pressure pulsation generated by fuel combustion is obtained through calculation, analysis or test measurement, at the moment, only a spray hole group at a specific axial position is selected to spray materials, the phase relation between the heat release rate pulsation and the pressure pulsation, namely the magnitude of delay time is regulated, so that the delay time is outside 1/4 of the oscillation period, the heat release rate pulsation and the pressure pulsation are not positively coupled, oscillation combustion is eliminated, and the combustion is recovered and stabilized.

In some embodiments, the nozzle groups at different axial positions are controlled by different valve switches, so that the nozzle groups at specific axial positions can be freely and flexibly selected to inject fuel under different oscillation combustion occurrence conditions, the flight time of the fuel reaching the flame front is regulated and controlled, the required delay time between the heat release rate pulsation and the pressure pulsation is obtained, the forward coupling of the heat release rate pulsation and the pressure pulsation is eliminated, the oscillation combustion is restrained, and the combustion is restored to a stable state.

Referring to FIG. 1, in some embodiments, the fuel nozzle 100 further includes 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. The structure is simple, and fuel sprayed by the fuel spray holes and the incoming flow passing through the first cyclone can be mixed in advance to form fuel spray for combustion.

In some embodiments, as shown in fig. 1, the normal direction b of the fuel nozzle 12 is perpendicular to the incoming flow direction c entering through the first swirler 301, so that the fuel is transversely sheared with the high-speed incoming flow after being injected from the fuel nozzle 12, and excellent fuel atomization and blending performance are obtained, so that full combustion is promoted, and pollutant emission is reduced. The "vertical" here need not be a strict 90 degree angle, but only requires the fuel to be sheared laterally from the high velocity incoming stream.

With continued reference to FIG. 1, in some embodiments, the fuel nozzle 100 may be specifically configured to include a main combustion stage 101 and a pre-combustion stage 102, the main combustion stage 101 including an annular chamber 201, at least a portion of the pre-combustion stage 102 being surrounded by the main combustion stage 101, the pre-combustion stage 102 including 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.

With continued reference to FIG. 1, in some embodiments, the pre-stage 102 may be specifically configured such that the pre-stage 102 includes a pre-stage nozzle 42 located at an axis of the annular body 41, the annular body 41 further having an inner ring portion 412, the inner ring portion 412 being provided with a second swirler 302, the second swirler 302 being in fluid communication with the pre-stage nozzle 42. The fuel is sprayed through the pre-stage nozzle 42 to form a pre-stage fuel spray 43, which is then blended with the incoming flow entering through the second swirler 302 to form a combustible blend. In some embodiments, as shown in FIG. 1, the second swirler 302 includes two-stage swirlers 3021, 3022 to increase the incoming flow rate to enable the pre-stage fuel spray 43 to burn sufficiently. While the annulus 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 outer ring 411 and the inner ring 412 may be single ring or multiple rings, for example, the outer ring 411 shown in the figure is a single ring, and the inner ring 412 is a multiple ring.

The main combustion stage and the precombustion stage are arranged to form staged combustion, the main combustion stage adopts a premixed combustion mode, and the precombustion stage adopts a diffusion combustion mode, so that the pollution emission of the engine can be effectively reduced. The premixed combustion of the main combustion stage has the advantages that the flame combustion temperature can be reduced, so that the NOx emission of a combustion chamber is reduced; the disadvantage is that the premixed fuel-air mixture is subject to air flow pressure disturbances, resulting in coupling between pressure pulsations and heat release rate pulsations, producing combustion oscillations. The annular chamber comprising the fuel ring is arranged on the main combustion stage, so that oscillation combustion can be effectively prevented and inhibited, combustion is stable, and safety is improved.

With continued reference to FIG. 1, in some embodiments, the fuel nozzle 100 may be specifically configured to further include a fuel delivery tube 5, the fuel delivery tube 5 being connected to an axial end of the annulus 11 of the fuel ring 1. The fuel enters the ring body 11 through the fuel delivery pipe 5 and then is delivered to each fuel spray hole 12 through the ring body 11, the number of the fuel spray holes 12 is generally a multiple of the number of groups corresponding to the spray hole groups, for example, the embodiment shown in the figure is provided with four spray hole groups 121, 122, 123 and 124, the number of spray holes of each spray hole group is the same, and the number of the spray holes of each spray hole group is 12 to 24, so that the processing of the fuel ring is easy, and the corresponding simulation calculation and calibration of the fuel spray nozzle are easy.

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

In some embodiments, as shown in fig. 1, the fuel nozzle 100 further includes a nozzle housing 7, a nozzle mount 8, one side of the nozzle housing 7 is connected to the annular outer wall 22 through a first swirler 301, the other side is connected to the nozzle mount 8, and the other ends of the fuel delivery pipe 5 and the pre-stage fuel delivery pipe 6 are in pipeline communication with the outside of the fuel nozzle 100 via the nozzle mount 8 to deliver fuel.

With continued reference to FIG. 1, in one embodiment, a specific structure for a combustor 1000 of a gas turbine engine may include a combustion vessel (not shown) and a fuel nozzle 100 as described above disposed adjacent to the combustion vessel. The downstream end of the annular chamber 201 of the fuel nozzle 100 is in direct communication with the combustion vessel and is configured to provide a flow of a fuel and air mixture to the combustion vessel. Specifically, as shown in fig. 1, the pre-combustion fuel enters the pre-combustion nozzle 42 through the pre-combustion fuel delivery pipe 6 and is sprayed out to form pre-combustion fuel spray 43, and the pre-combustion air interacts with the pre-combustion fuel spray 43 after passing through the two-stage swirler to form combustible blending gas, so that the pre-combustion fuel is supplied and fully atomized and blended, and is sprayed to the combustion container. The main combustion grade fuel enters the ring body 11 through the fuel delivery pipe 5, then the fuel is delivered to the fuel spray holes 12 through the ring body 11 and is sprayed out through the fuel spray holes 12, the main combustion grade air generates rotational flow through the first rotational flow device 301 and is sheared at a high speed with the fuel sprayed from the fuel spray holes 12 to the direction b, so that the atomization of the main combustion grade fuel is realized, and the main combustion grade fuel spray 44 is formed and sprayed to the combustion container.

The beneficial effect of this arrangement is that the combustion chamber employing the fuel nozzle 100 described above can prevent and eliminate combustion oscillations, improving combustion stability of the combustion chamber.

In one embodiment, a specific structure of the gas turbine engine may be to include the combustor 1000 as described above. The combustion chamber can effectively inhibit oscillation combustion, ensure stable operation of the engine and improve safety of the engine.

Referring to fig. 1-5, in one embodiment, the specific steps of a method for suppressing oscillating combustion for a gas turbine engine may be, including: a main combustion stage 101 is provided, the main combustion stage 101 being arranged to: injecting into the main combustion stage 101 through a plurality of fuel injection holes 12 positioned 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, and the injection hole groups 121, 122, 123, 124 are arranged on the ring body 11 in an annular arrangement manner to form a plurality of coaxial annular shapes 1210, 1220, 1230, 1240 distributed along the axial direction of the ring body 11; when the oscillating combustion occurs, the nozzle hole groups are selectively formed into at least one combination, and the nozzle hole groups other than the combination are closed to suppress the oscillating combustion. The specific principle is that as the spray hole groups 121, 122, 123 and 124 have different axial positions, after combustion oscillation occurs in the combustion chamber, the phase difference between heat release rate pulsation and pressure pulsation generated by fuel combustion is obtained through calculation, analysis or test measurement, only a specific spray hole group is selected to be opened for spraying materials at the moment, the phase relation between the heat release rate pulsation and the pressure pulsation of the combustion chamber, namely the delay time of the heat release rate pulsation and the pressure pulsation is adjusted, so that the delay time of the heat release rate pulsation and the pressure pulsation is outside 1/4 oscillation period, the flight time of most of the fuel spray holes under any operation working condition of the engine is not in the 1/4 phase difference range of oscillation frequency, combustion oscillation caused by heat-sound forward coupling is eliminated, stable combustion is realized, and meanwhile, the arrangement of a plurality of fuel spray holes does not influence the combustion performance under the working condition, and the normal operation of the engine is ensured.

With the above description in mind, it will be appreciated by those skilled in the art that a fuel ring for a fuel turbine engine may be sold as an engine accessory with the engine as a whole or manufactured and sold as a separate product and therefore is also within the scope of the present application. Referring to fig. 2 to 5, in one embodiment, a specific structure of a fuel ring 1 for a fuel turbine engine may include a ring body 11 and a plurality of fuel injection holes 12, the plurality of fuel injection holes 12 being distributed along a circumferential direction of the ring body 11, an injection direction of the plurality of fuel injection holes 12 being radial; the plurality of fuel injection holes 12 at least includes injection hole groups 121, 122, 123, 124 having different axial positions, the injection hole groups 121, 122, 123, 124 are disposed in the ring body 11 in an annular arrangement, forming a plurality of coaxial annular shapes 1210, 1220, 1230, 1240 distributed along the axial direction of the ring body 11, and the injection hole groups 121, 122, 123, 124 may be selectively combined to form at least one combination that suppresses oscillations. The fuel ring can regulate and control the delay time of fuel reaching the flame front to participate in combustion after being sprayed out from the fuel spray holes, so that the flight time of most of the fuel spray holes is not in the range of the thermal-acoustic normal phase coupling phase difference under any operating condition of the engine, the thermal-acoustic coupling strength is weakened, the combustion stability of the combustion chamber of the engine is enhanced, the stable operation of the engine is ensured, and the safety of the engine is improved.

In summary, the beneficial effects of the gas turbine engine, fuel nozzles, combustors, fuel rings and methods of suppressing oscillations of combustion for use with the above embodiments include, but are not limited to, one or a combination of the following:

1. the fuel nozzle has the advantages that the jet hole groups at different axial positions are arranged, so that fuels jetted from the different jet hole groups have different flight times from the jet position to the flame frontal surface, the delay time distribution range between the heat release rate pulsation and the pressure pulsation is further enlarged, the probability of occurrence of same-phase forward coupling of the combustion heat release rate pulsation and the pressure pulsation of the fuel in the combustion chamber is reduced, the risk of occurrence of combustion oscillation is reduced, and a preventive effect is achieved. Meanwhile, different jet orifice groups can be selectively combined, so that the time distribution required by transporting fuel from the jet orifice to the flame front is regulated and controlled, the delay time between the heat release rate pulsation and the pressure pulsation is not in the 1/4 phase difference range of the oscillation frequency, the combustion oscillation caused by the heat-sound coupling is eliminated, the stable combustion is realized, and the inhibition effect is realized. And the fuel supply quantity under the corresponding working condition can be ensured by arranging the spray hole group, so that the combustion performance is not influenced.

2. The combustion chamber adopting the fuel nozzle can prevent and eliminate combustion oscillation and improve the combustion stability of the combustion chamber.

3. The gas turbine engine adopting the combustion chamber can effectively inhibit oscillation combustion, ensure stable operation of the engine and improve the safety of the engine.

4. By adopting the method for suppressing oscillation combustion of the gas turbine engine, the delay time of heat release rate pulsation and pressure pulsation can be regulated and controlled, so that combustion oscillation caused by heat-sound forward coupling is eliminated, stable combustion is realized, and meanwhile, the arrangement of a plurality of fuel spray holes does not influence the combustion performance under the working condition, and the normal operation of the engine is ensured.

5. The fuel ring can regulate and control the delay time of fuel reaching the flame front to participate in combustion after being sprayed out from the fuel spray holes, so that the flight time of most fuel spray holes is not in the range of thermal-acoustic normal phase coupling phase difference under any operating condition of the engine, the thermal-acoustic coupling strength is weakened, the combustion stability of the combustion chamber of the engine is enhanced, the stable operation of the engine is ensured, and the safety of the engine is improved.

While the application has been described in terms of preferred embodiments, it is not intended to be limiting, but rather to the application, as will occur to those skilled in the art, without departing from the spirit and scope of the application. Therefore, any modification, equivalent variation and modification of the above embodiments according to the technical substance of the present application fall within the protection scope defined by the claims of the present application.

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.