Gas turbine engine and fuel nozzle, combustion chamber, fuel ring and method for suppressing oscillatory combustion therefor

Abstract

The present application provides a kind of gas turbine engine and the fuel nozzle for it, combustion chamber, fuel ring and inhibiting oscillating combustion method.Therein fuel nozzle includes: fuel ring, including ring body and multiple fuel injection holes, multiple fuel injection holes are distributed along the circumference of ring body, the injection direction of multiple fuel injection holes is radial;Annular inner wall;Annular outer wall, at least part of annular inner wall is formed annular chamber around;Wherein multiple fuel injection holes at least include the injection hole group with different axial positions, injection hole group, in the form of annular arrangement is arranged in ring body, forms multiple coaxial annular along the axial distribution of ring body, injection hole group, can be selectively combined, to form at least one combination of inhibiting oscillating combustion.Oscillating combustion is inhibited.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aeroengines, in particular to a gas turbine engine and a fuel nozzle, a combustion chamber, a fuel ring and a method for suppressing oscillatory combustion used therein. BACKGROUND

[0002] Modern low-pollution lean-burn engine combustion chambers are prone to combustion oscillation phenomenon, which affects the safe and stable operation of gas turbines and aeroengines. The oscillation can further cause vibration of the engine structure, limit the rise of engine speed and load, induce extinction and backfire, cause failure of engine components, explosion and other serious consequences. In addition, during the development of aeroengines and gas turbines, the development process of components and the whole machine is often affected by the occurrence of thermal-acoustic oscillation phenomenon, delaying the progress of project development. SUMMARY

[0003] The purpose of the present application is to provide a fuel nozzle for a gas turbine engine.

[0004] Another purpose of the present application is to provide a combustion chamber for a gas turbine engine.

[0005] Still another purpose of the present application is to provide a gas turbine engine.

[0006] Still another purpose of the present application is to provide a method for suppressing oscillatory combustion of a gas turbine engine.

[0007] Still another purpose of the present application is to provide a fuel ring for a gas turbine engine.

[0008] According to one aspect of the present application, a fuel nozzle for a gas turbine engine comprises: a fuel ring comprising a ring body and a plurality of fuel injection holes, the plurality of fuel injection holes being distributed along the circumference of the ring body, the injection direction of the plurality of fuel injection holes being 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 comprises at least a group of injection holes having different axial positions, the group of injection holes is arranged in a ring shape on the ring body, forming a plurality of coaxial annulars distributed along the axial direction of the ring body, and the group of injection holes can be selectively combined to form at least one combination for suppressing oscillatory combustion.

[0009] The technical scheme of the present application sets different axial position groups of injection holes, so that the fuel injected from different groups of injection holes has different flight times from the injection position to the flame front, thereby increasing the delay time distribution range between the heat release rate fluctuation and the pressure fluctuation, reducing the probability of positive phase coupling of the fuel combustion heat release rate fluctuation and the pressure fluctuation in the combustion chamber, reducing the risk of combustion oscillation, and playing a preventive role. At the same time, different groups of injection holes can be selectively combined to control the time distribution required for fuel transportation from the injection holes to the flame front, so that the delay time between the heat release rate fluctuation and the pressure fluctuation is not within the 1 / 4 phase difference range of the oscillation frequency, eliminating the combustion oscillation caused by heat-sound coupling, achieving stable combustion, and playing a suppression role. And because the groups of injection holes are set, the fuel supply amount under the corresponding working condition can be ensured, and the combustion performance will not be affected.

[0010] In one or more embodiments of the fuel nozzle, the fuel injection holes extend radially outward from the annular body of the fuel ring.

[0011] In one or more embodiments of the fuel nozzle, each of the groups of injection holes includes a plurality of fuel injection holes that are uniformly distributed circumferentially.

[0012] In one or more embodiments of the fuel nozzle, the plurality of coaxial annular rings are located at a first axial position, a second axial position, a third axial position, and a fourth axial position, respectively.

[0013] In one or more embodiments of the fuel nozzle, the first axial position, the second axial position, the third axial position, and the fourth axial position are equally spaced in the axial direction.

[0014] In one or more embodiments of the fuel nozzle, the first axial position, the second axial position, the third axial position, and the fourth axial position have an axial spacing L that satisfies the condition L / V = T / 8, where V is the velocity of fuel particles and T is the period of combustion oscillation.

[0015] 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 of the fuel injection holes of the groups of injection holes of the fuel ring are in an open state; in the second state, part of the fuel injection holes of the groups of injection holes of the fuel ring are in a closed state, and the remaining groups of injection holes form the combination to form the oscillation-suppressed combustion.

[0016] In one or more embodiments of the fuel nozzle, the fuel nozzle further includes a first swirler located upstream of the annular chamber and in fluid communication with the plurality of fuel injection holes.

[0017] In one or more embodiments of the fuel nozzle, the fuel nozzle comprises a main stage and a pilot stage, the main stage comprising the annular chamber, at least a portion of the pilot stage being surrounded by the main stage, the pilot stage comprising an annular body having an outer ring portion constituting an annular inner wall of the annular chamber.

[0018] In one or more embodiments of the fuel nozzle, the pilot stage comprises a pilot stage nozzle located at an axis of the annular body, the annular body further having an inner ring portion provided with a second swirler in fluid communication with the pilot stage nozzle.

[0019] In one or more embodiments of the fuel nozzle, further comprising a fuel delivery tube connected to an axial end of the ring body of the fuel ring.

[0020] According to yet another aspect of the present application, a combustor for a gas turbine engine comprises: a combustion vessel; and a fuel nozzle as claimed in any one of the preceding 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, configured to provide a flow of fuel and air mixture to the combustion vessel.

[0021] According to yet another aspect of the present application, a gas turbine engine comprises a combustor as claimed above.

[0022] According to yet another aspect of the present application, a method for suppressing oscillatory combustion in a gas turbine engine comprises: providing a main stage configured to be injected into the main stage through a plurality of fuel injection holes located in the main stage, wherein the plurality of fuel injection holes comprises at least a group of injection holes having different axial positions, the group of injection holes being arranged in an annular arrangement on a ring body to form a plurality of coaxial annulars distributed along an axial direction of the ring body; when oscillatory combustion occurs, the group of injection holes is selectively formed into at least one combination, and the injection holes outside the combination are closed to suppress oscillatory combustion.

[0023] According to yet another aspect of the present application, a fuel ring for a gas turbine engine comprises a ring body and a plurality of fuel injection holes distributed along a circumferential direction of the ring body, the plurality of fuel injection holes having a radial injection direction; the plurality of fuel injection holes comprises at least a group of injection holes having different axial positions, the group of injection holes being arranged in an annular arrangement on the ring body to form a plurality of coaxial annulars distributed along an axial direction of the ring body, the group of injection holes being selectively combinable to form at least one combination for suppressing oscillation. BRIEF DESCRIPTION OF DRAWINGS

[0024] The above and other characteristics, features and advantages of the present application will become apparent from the following description, taken in conjunction with the accompanying drawings, which illustrate, by way of example, the principles of the application. It is to be understood that this

[0025] Figure 1 Cross-sectional view of a fuel nozzle according to an embodiment;

[0026] Figure 2 Structure view of a fuel nozzle according to an embodiment;

[0027] Figure 3 Structure view of a fuel nozzle according to an embodiment from another perspective;

[0028] Figure 4 Structure view of a fuel ring according to an embodiment;

[0029] Figure 5 Cross-sectional view of a fuel ring according to an embodiment.

[0030] Reference signs:

[0031] 1000 - combustion chamber;

[0032] 100 - fuel nozzle;

[0033] 101 - main stage, 44 - main stage fuel spray;

[0034] 102 - pilot stage, 41 - annular body, 411 - outer ring portion, 412 - inner ring portion, 42 - pilot stage nozzle, 43 - pilot stage fuel spray;

[0035] 1 - fuel ring, 11 - ring body, 1210, 1220, 1230, 1240 - coaxial annular, 12 - fuel injection hole, 121, 122, 123, 124 - injection hole group;

[0036] A1 - first axial position, A2 - second axial position, A3 - third axial position, A4 - fourth axial position;

[0037] 21 - annular inner wall, 22 - annular outer wall, 201 - annular chamber;

[0038] 301 - first swirler, 302 - second swirler, 3021, 3022 - two-stage swirler;

[0039] 5 - fuel delivery pipe, 6 - pilot stage fuel delivery pipe;

[0040] 7 - nozzle housing, 8 - nozzle mounting seat. Detailed Implementation

[0041] Reference will now be made in detail to various embodiments of the invention, examples of which are shown in the accompanying drawings and described below. Although the invention will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to those exemplary embodiments. Rather, the invention is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims.

[0042] In the following description, the terms "radial," "axial," "circumferential," "inner," "outer," "upstream," "downstream," or other directional terms indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These are used solely for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, "upstream" and "downstream" are distinguished based on the direction of fuel flow; specifically, fuel flows from "upstream" to "downstream."

[0043] Furthermore, this application uses specific terms to describe its embodiments. For example, "an embodiment" and / or "one embodiment" refers to a particular feature, structure, or characteristic associated with at least one embodiment of this application. Therefore, it should be emphasized and noted that "an embodiment" or "one embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of this application can be appropriately combined.

[0044] Currently, with increasingly higher requirements for low-pollution emissions and combustion stability in engine combustion chambers, there is a need to further improve the performance of combustion chambers.

[0045] The inventors of this application, through in-depth research, discovered that combustion oscillation in the combustion chamber is extremely harmful. Combustion oscillation manifests as periodic oscillations in the heat release rate and dynamic pressure generated by fuel combustion within the combustion chamber, exhibiting significant amplitude. 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, positive coupling occurs between the two, leading to combustion oscillation. For aero-engine combustion chambers using liquid fuel, the delay time between heat release rate pulsation and pressure pulsation is primarily determined by four factors: the time required for fuel atomization, fuel evaporation, the transport of combustible mixture from the nozzle to the flame front, and the time required for chemical reaction. Since the times required for fuel atomization, evaporation, and chemical reaction are inherent properties of the fuel itself, they are difficult to control.

[0046] Based on the above considerations, the inventors have conducted in-depth research in order to regulate the delay time between the heat release rate pulsation and the pressure pulsation and ultimately decouple the two, thereby inhibiting the generation of combustion oscillation. The inventors have designed a fuel nozzle for a gas turbine engine, by providing different groups of injection holes at different axial positions, so that the fuel injected from different groups of injection holes has different flight times from the injection position 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 in-phase positive coupling of the fuel combustion heat release rate pulsation and the pressure pulsation in the combustion chamber, reducing the risk of combustion oscillation, and playing a preventive role. At the same time, different groups of injection holes can be selectively combined to regulate the time distribution required for fuel transport from the injection holes to the flame front, so that the delay time between the heat release rate pulsation and the pressure pulsation is not within the 1 / 4 phase difference range of the oscillation frequency, eliminating combustion oscillation caused by heat-sound coupling, achieving stable combustion, and playing an inhibitory role. Moreover, the provision of groups of injection holes can ensure the fuel supply under the corresponding working conditions, without affecting the combustion performance.

[0047] Although the fuel nozzle disclosed in the embodiments of the present application is suitable for a gas turbine engine to achieve the effect of inhibiting oscillatory combustion, it is not limited thereto, and can be applied to any engine.

[0048] The following embodiments introduce aviation kerosene as an example of fuel, but are not limited thereto.

[0049] Reference Figure 1 In combination Figure 2 As shown in the figure, in one embodiment, the specific structure of the fuel nozzle 100 for a gas turbine engine can be as follows: it comprises a fuel ring 1, an annular inner wall 21, and an annular outer wall 22. The fuel ring 1 comprises a ring body 11 and a plurality of fuel injection holes 12, which are distributed along the circumference 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. Among them, the plurality of fuel injection holes 12 at least comprises groups of injection holes 121, 122, 123, 124 having different axial positions, the groups of injection holes 121, 122, 123, 124 are arranged in a ring shape and are arranged on the ring body 11, forming a plurality of coaxial annular rings 1210, 1220, 1230, 1240 distributed along the axial direction of the ring body 11, and the groups of injection holes 121, 122, 123, 124 can be selectively combined to form at least one combination for inhibiting oscillatory combustion.

[0050] Here, the "plurality of coaxial annular rings 1210, 1220, 1230, 1240" is, for example Figure 2 , Figure 3 As shown in the figure, the annular rings 1210, 1220, 1230, 1240 have the same axis a.

[0051] The meaning of "the injection hole groups 121, 122, 123, 124 can be selectively combined to form at least one combination for suppressing oscillatory combustion" here is specifically referring to that the injection hole groups can be all opened or partially opened and partially closed, and the combination of the injection hole groups is performed according to the actual oscillatory combustion. For example, as shown in the figure, one combination can be opening the injection hole groups 121, 124 and closing the injection hole groups 122, 123, and another combination can be opening the injection hole group 122 and closing the remaining injection hole groups, and the above two combination examples are not limited, and other types of combinations can also be available according to different situations. Figure 3 、 Figure 4 The meaning of "the injection hole groups 121, 122, 123, 124 can be selectively combined to form at least one combination for suppressing oscillatory combustion" here is specifically referring to that the injection hole groups can be all opened or partially opened and partially closed, and the combination of the injection hole groups is performed according to the actual oscillatory combustion. For example, as shown in the figure, one combination can be opening the injection hole groups 121, 124 and closing the injection hole groups 122, 123, and another combination can be opening the injection hole group 122 and closing the remaining injection hole groups, and the above two combination examples are not limited, and other types of combinations can also be available according to different situations.

[0052] The beneficial effect of this is that, by setting injection hole groups at different axial positions, the fuel injected from different injection hole groups has different flight times from the injection position 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 positive coupling of the same phase of the heat release rate pulsation and the pressure pulsation in the combustion chamber, reducing the risk of combustion oscillation, and playing a preventive role. At the same time, different injection hole groups can be selectively combined, and the injection direction of the fuel injection hole is radial, which is convenient for regulating the time distribution required for the fuel to be transported from the injection hole to the flame front, so that once oscillatory combustion occurs, the delay time between the heat release rate pulsation and the pressure pulsation can be quickly adjusted to not be within the 1 / 4 phase difference range of the oscillation frequency, eliminating the combustion oscillation caused by heat-sound coupling, thereby quickly eliminating the oscillatory combustion phenomenon and achieving stable combustion. At the same time, the structure of the fuel ring and the injection hole makes the combination of the injection hole groups not affect the total fuel supply amount of the fuel nozzle, only the fuel supply amount corresponding to each injection hole group changes, and does not affect the combustion performance.

[0053] Referring to Figure 5 In some embodiments, the specific structure of the fuel injection hole 12 can be that the fuel injection hole 12 extends radially outward from the ring body 11 of the fuel ring 1. The "ring body 11" here is a hollow structure, and the fuel first fills the ring body 11 and then is injected out by the fuel injection hole 12. The beneficial effect of such a setting is that it is convenient for selectively combining and controlling different injection hole groups, achieving precise regulation of the delay time between the heat release rate pulsation and the pressure pulsation, and effectively playing a role in suppressing oscillatory combustion.

[0054] Referring to Figures 2 to 4As shown in some embodiments, the specific structure of the fuel injection holes 12 can be that the multiple fuel injection holes 12 included in each injection hole group 121, 122, 123, 124 are uniformly distributed in the circumferential direction. The beneficial effect of such an arrangement is that it can make the fuel injected into the annular chamber uniformly distributed, and thus the time at which the pressure pulsation and heat release rate pulsation respectively generated at different locations are substantially the same, facilitating calculation and analysis and selective combination of different injection hole groups for controlling the oscillation combustion.

[0055] As shown in some embodiments, Figures 2 to 5 As shown, the circumferential positions of the adjacent fuel injection holes 12 are alternately distributed, which can make the fuel of each injection hole group uniformly distributed and ensure the uniformity of combustion.

[0056] As shown in some embodiments, Figure 3 As shown in some embodiments, the specific structure of the fuel injection holes 12 can be that the multiple fuel injection holes 12 included in each injection hole group 121, 122, 123, 124 are uniformly distributed in the circumferential direction. The beneficial effect of such an arrangement is that it can make the fuel injected into the annular chamber uniformly distributed, and thus the time at which the pressure pulsation and heat release rate pulsation respectively generated at different locations are substantially the same, facilitating calculation and analysis and selective combination of different injection hole groups for controlling the oscillation combustion.

[0057] As shown in some embodiments, Figure 3 As shown, the circumferential positions of the adjacent fuel injection holes 12 are alternately distributed, which can make the fuel of each injection hole group uniformly distributed and ensure the uniformity of combustion.

[0058] As shown in some embodiments, Figure 3 As shown, the circumferential positions of the adjacent fuel injection holes 12 are alternately distributed, which can make the fuel of each injection hole group uniformly distributed and ensure the uniformity of combustion.

[0059] Here, the "combustion oscillation period T" is determined according to the frequency of combustion oscillation. Assuming that the frequency of combustion oscillation is f, the corresponding combustion oscillation period T is T = 1 / f.

[0060] Here, the "axial spacing L satisfies: L / V = T / 8" is based on the principle of controlling the flight time difference of fuel injected from adjacent fuel injection holes to the flame surface to be 1 / 8 of the combustion oscillation period.

[0061] The beneficial effect of the arrangement is that the delay time between the heat release rate fluctuation and the pressure fluctuation is located outside the 1 / 4 oscillation period, the heat release rate fluctuation and the pressure fluctuation are prevented from being positively coupled, the frequency of the occurrence of the combustion oscillation is reduced, the combustion oscillation is eliminated when the oscillation combustion occurs, and stable combustion is ensured.

[0062] Referring to Figures 1 to 5 As shown in some embodiments, the specific structure of the fuel nozzle 100 can be that the fuel nozzle 100 includes a first state and a second state:

[0063] In the first state, all of the fuel injection holes 12 of the fuel injection hole groups 121, 122, 123, 124 of the fuel ring 1 are in an open state. At this time, the combustion is in a stable state.

[0064] In the second state, part of the fuel injection holes 12 of the fuel injection hole groups 121, 122, 123, 124 of the fuel ring 1 are in a closed state, and the remaining fuel injection hole groups 121, 122, 123, 124 are combined to form an oscillation suppression combustion. At this time, the combustion is in an oscillation state.

[0065] The principle is that when the combustion oscillation occurs, the phase difference between the heat release rate fluctuation and the pressure fluctuation generated by the fuel combustion is obtained by calculation analysis or experimental measurement, at this time, only the fuel injection hole groups at a specific axial position are selected to be opened, the phase relationship between the heat release rate fluctuation and the pressure fluctuation, that is, the size of the delay time, is adjusted, so that the delay time is located outside the 1 / 4 oscillation period, so that the heat release rate fluctuation and the pressure fluctuation are not positively coupled, the oscillation combustion is eliminated, and the combustion is restored to a stable state.

[0066] In some embodiments, the fuel injection hole groups at different axial positions are controlled by different valve switches, so that the fuel injection hole groups at a specific axial position are freely and flexibly selected under different oscillation combustion occurrence conditions, and the flight time of the fuel to the flame front is regulated, the required delay time between the heat release rate fluctuation and the pressure fluctuation is obtained, the positive coupling of the heat release rate fluctuation and the pressure fluctuation is eliminated, the oscillation combustion is suppressed, and the combustion is restored to a stable state.

[0067] Referring to Figure 1 As shown 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. The structure is simple, and the fuel injected by the fuel injection holes can be pre-mixed with the flow passing through the first swirler to form a fuel spray for combustion.

[0068] In some embodiments, as Figure 1As shown, the normal direction b of the fuel injection hole 12 is perpendicular to the incoming flow direction c through the first swirler 301, so that the fuel jetted out of the fuel injection hole 12 is subjected to transverse shearing with the high-speed incoming flow, thereby achieving excellent fuel atomization and mixing performance, promoting full combustion, and reducing pollutant emissions. Here, "perpendicular" does not necessarily mean a strict 90-degree angle, but only requires that the fuel is subjected to transverse shearing with the high-speed incoming flow.

[0069] With continued reference to Figure 1 As shown, in some embodiments, the specific structure of the fuel nozzle 100 can be that it includes a main combustion stage 101 and a pre-combustion stage 102, the main combustion stage 101 includes an annular chamber 201, at least part of the pre-combustion stage 102 is surrounded by the main combustion stage 101, and the pre-combustion stage 102 includes an annular body 41 having an outer ring portion 411 constituting an annular inner wall 21 of the annular chamber 201.

[0070] With continued reference to Figure 1 As shown, in some embodiments, the specific structure of the pre-combustion stage 102 can be that the pre-combustion stage 102 includes a pre-combustion stage nozzle 42 located at the axis of the annular body 41, and the annular body 41 further has an inner ring portion 412 provided with a second swirler 302 in fluid communication with the pre-combustion stage nozzle 42. Fuel is jetted out of the pre-combustion stage nozzle 42 to form a pre-combustion stage fuel spray 43, which is then mixed with the incoming flow through the second swirler 302 to form a combustible mixed gas. In some embodiments, as Figure 1 As shown, the second swirler 302 includes two-stage swirler 3021, 3022 to increase the flow rate so that the pre-combustion stage fuel spray 43 can be fully combusted. 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 portion 411 and the inner ring portion 412 can be a single ring body or multiple ring bodies, for example, the outer ring portion 411 is a single ring body structure and the inner ring portion 412 is a multiple ring body structure as shown in the figure.

[0071] The arrangement of the main combustion stage and the pre-combustion stage constitutes a staged combustion, the main combustion stage adopts a premixed combustion mode, and the pre-combustion stage adopts a diffusion combustion mode, which can effectively reduce engine pollution emissions. The premixed combustion of the main combustion stage has the advantage of reducing flame combustion temperature, thereby reducing the NOx emission of the combustion chamber; the disadvantage is that the premixed fuel-air mixture is easily disturbed by airflow pressure, causing coupling between pressure pulsation and heat release rate pulsation, resulting in combustion oscillation. The annular chamber including the above-mentioned fuel ring arranged in the main combustion stage can effectively prevent and suppress oscillatory combustion, stabilize combustion, and improve safety.

[0072] With continued reference to Figure 1As shown, in some embodiments, the specific structure of the fuel nozzle 100 can be further provided with a fuel delivery pipe 5 connected to the axial end of the ring body 11 of the fuel ring 1. Fuel enters the ring body 11 through the fuel delivery pipe 5, and then is delivered to the fuel injection holes 12 through the ring body 11. The number of fuel injection holes 12 is generally a multiple of the number of groups of injection holes, for example, the embodiment shown in the figure has four groups of injection holes 121, 122, 123, 124, and the number of injection holes in each group of injection holes is the same, and the total number of fuel injection holes is 12 to 24. This facilitates the processing of the fuel ring and the corresponding simulation and calibration of the fuel nozzle.

[0073] In some embodiments, as shown in Figure 1 The fuel nozzle 100 further comprises a pre-combustion stage fuel delivery pipe 6 connected to the axial end of the pre-combustion stage nozzle 42.

[0074] In some embodiments, as shown in Figure 1 The fuel nozzle 100 further comprises 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 mounting seat 8. The other end of the fuel delivery pipe 5 and the pre-combustion stage fuel delivery pipe 6 communicates with the outer pipeline of the fuel nozzle 100 through the nozzle mounting seat 8 to deliver fuel.

[0075] Continuing to refer to Figure 1 As shown in one embodiment, the specific structure of the combustion chamber 1000 for a gas turbine engine can be provided with a combustion vessel (not shown in the figure) and a fuel nozzle 100 as described above arranged adjacent to the combustion vessel. The downstream end of the annular chamber 201 of the fuel nozzle 100 directly communicates with the combustion vessel and is configured to provide a flow of fuel and air mixture to the combustion vessel. In particular, as Figure 1 As shown, the pre-combustion stage fuel enters the pre-combustion stage nozzle 42 through the pre-combustion stage fuel delivery pipe 6 and is ejected to form a pre-combustion stage fuel spray 43. The pre-combustion stage air interacts with the pre-combustion stage fuel spray 43 after passing through the two-stage swirler to form a combustible mixture, achieving the supply and sufficient atomization and mixing of the pre-combustion stage fuel, which is injected into the combustion vessel. The main combustion stage fuel enters the ring body 11 through the fuel delivery pipe 5, and then is delivered to the fuel injection holes 12 through the ring body 11 and ejected through the fuel injection holes 12. The main combustion stage air generates a swirl through the first swirler 301 and is subjected to high-speed shearing with the fuel ejected through the fuel injection holes 12 in the normal direction b, achieving the atomization of the main combustion stage fuel to form a main combustion stage fuel spray 44, which is injected into the combustion vessel.

[0076] The beneficial effects of such an arrangement are that the combustion chamber using the above-mentioned fuel nozzle 100 can prevent and eliminate combustion oscillation, improving the combustion stability of the combustion chamber.

[0077] In one embodiment, the specific structure of the gas turbine engine can be a combustor 1000 as described above. The use of the combustor as described above can effectively suppress oscillatory combustion, ensure stable operation of the engine, and improve the safety of the engine.

[0078] Reference Figures 1 to 5 As shown, in one embodiment, the specific steps of the method for suppressing oscillatory combustion of a gas turbine engine can include: providing a main combustion stage 101, which is configured to inject fuel 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 include a plurality of injection hole groups 121, 122, 123, 124 having different axial positions, and the injection hole groups 121, 122, 123, 124 are arranged in a ring shape on the 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 oscillatory combustion occurs, the injection hole groups are selectively formed into at least one combination, and the injection hole groups outside the combination are closed to suppress oscillatory combustion. The specific principle is that, since the injection hole groups 121, 122, 123, 124 have different axial positions, when the combustor experiences combustion oscillation, the phase difference between the heat release rate fluctuation and the pressure fluctuation generated by fuel combustion is obtained through calculation analysis or experimental measurement, at this time, only the specific injection hole group is selected to open the fuel injection, the phase relationship between the heat release rate fluctuation and the pressure fluctuation of the combustor is adjusted, i.e. the delay time of the two, so that the delay time of the two is located outside the 1 / 4 oscillation period, the flight time of most fuel injection holes under any operating condition of the engine is not within the 1 / 4 phase difference range of the oscillation frequency, the combustion oscillation caused by heat-acoustic positive coupling is eliminated, stable combustion is achieved, and the setting of the plurality of fuel injection holes and the non-impact on the combustion performance under this condition ensure the normal operation of the engine.

[0079] Based on the above description, those skilled in the art can understand that the fuel ring for the fuel turbine engine can be sold as a part of the engine together with the engine as a whole, or it can be manufactured and sold as a separate product, therefore the fuel ring for the fuel turbine engine also belongs to the protection scope of the present application. Figures 2 to 5As shown, in one embodiment, the specific structure of the fuel ring 1 for the fuel turbine engine can be that it comprises a ring body 11 and a plurality of fuel injection holes 12 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 having different axial positions, the injection hole groups 121, 122, 123, 124 are arranged in a ring shape on the ring body 11, forming 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. The fuel ring using the embodiment can regulate the delay time of fuel from the fuel injection hole to the flame front after being injected, so that the flight time of most fuel injection holes under any operating condition of the engine is not within the range of the positive phase difference of thermal-acoustic coupling, the strength of thermal-acoustic coupling is weakened, the combustion stability of the engine combustion chamber is enhanced, the stable operation of the engine is ensured, and the safety of the engine is improved.

[0080] In summary, the beneficial effects of the gas turbine engine and the fuel nozzle, the combustion chamber, the fuel ring and the oscillation-suppressed combustion method introduced in the above embodiments include one or a combination of the following:

[0081] 1. The fuel nozzle sets different axial position injection hole groups, so that the fuel injected from different injection hole groups has different flight times from the injection position to the flame front, thereby increasing the delay time distribution range between the heat release rate fluctuation and the pressure fluctuation, reducing the probability of positive phase coupling of the fuel combustion heat release rate fluctuation and the pressure fluctuation in the combustion chamber, reducing the risk of combustion oscillation, and playing a preventive role. At the same time, different injection hole groups can be selectively combined to regulate the time distribution required for fuel transportation from the injection hole to the flame front, so that the delay time between the heat release rate fluctuation and the pressure fluctuation is not within the 1 / 4 phase difference range of the oscillation frequency, eliminating the combustion oscillation caused by thermal-acoustic coupling, realizing stable combustion, and playing a suppression role. Moreover, setting the injection hole groups can ensure the fuel supply under the corresponding working condition, without affecting the combustion performance.

[0082] 2. The combustion chamber using the above-mentioned fuel nozzle can prevent and eliminate combustion oscillation, and improve the combustion stability of the combustion chamber.

[0083] 3. The gas turbine engine using the above-mentioned combustion chamber can effectively suppress oscillation combustion, ensure the stable operation of the engine, and improve the safety of the engine.

[0084] 4. The method for suppressing oscillating combustion of the gas turbine engine can regulate the delay time of heat release rate fluctuation and pressure fluctuation, thereby eliminating the combustion oscillation caused by heat-acoustic positive coupling, realizing stable combustion, and ensuring normal operation of the engine.

[0085] 5. The fuel ring of the present application can regulate the delay time of fuel from the fuel injection hole to the flame front to participate in combustion, so that the flight time of most fuel injection holes under any operating condition of the engine is not within the range of the phase difference of heat-acoustic positive coupling, the strength of heat-acoustic coupling is weakened, the combustion stability of the engine combustion chamber is enhanced, the stable operation of the engine is ensured, and the safety of the engine is improved.

[0086] Although the present application is disclosed with the preferred embodiments as above, it is not intended to limit the present application, and any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present application. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application, which does not deviate from the technical solutions of the present application, falls within the protection scope defined by the claims of the present application.

Claims

1. A fuel nozzle (100) for a gas turbine engine, characterized in that, include: A fuel ring (1) includes a ring body (11) and a plurality of fuel injection holes (12), wherein the plurality of fuel injection holes (12) are distributed circumferentially along the ring body (11) and the injection direction of the plurality of fuel injection holes (12) is radial; Annular inner wall (21); An annular outer wall (22) forms an annular chamber (201) surrounding at least a portion of the annular inner wall (21); The plurality of fuel injection holes (12) includes at least a group of injection holes (121, 122, 123, 124) with different axial positions. The injection hole groups (121, 122, 123, 124) are arranged in a ring on the ring body (11) to form a plurality of coaxial rings (1210, 1220, 1230, 1240) distributed along the axial direction of the ring body (11). The plurality of coaxial rings (1210, 1220, 1230, 1240) are respectively located at a first axial position (A1), a second axial position (A2), and a third axial position (A3). The first axial position (A1), the second axial position (A2), the third axial position (A3), and the fourth axial position (A4) are distributed at equal intervals in the axial direction. The axial spacing L of the first axial position (A1), the second axial position (A2), the third axial position (A3), and the fourth axial position (A4) satisfies: L / V = T / 8, where V is the velocity of the fuel particles and T is the combustion oscillation period. The nozzle groups (121, 122, 123, 124) can be selectively combined to form at least one combination that suppresses oscillating combustion.

2. The fuel nozzle (100) as claimed in claim 1, characterized in that, The fuel nozzle (12) extends radially outward from the ring body (11) of the fuel ring (1).

3. The fuel nozzle (100) as claimed in claim 1, characterized in that, Each of the nozzle groups (121, 122, 123, 124) includes a plurality of fuel nozzles (12) that are uniformly distributed circumferentially.

4. The fuel nozzle (100) as claimed in claim 1, characterized in that, The fuel nozzle (100) includes a first state and a second state: In the first state, the fuel nozzles (12) of all the nozzle groups (121, 122, 123, 124) of the fuel ring (1) are in the open state; In the second state, the fuel nozzles (12) of a portion of the nozzle group (121, 122, 123, 124) of the fuel ring (1) are closed, and the remaining nozzle groups (121, 122, 123, 124) constitute the combination to form a suppression of oscillating combustion.

5. The fuel nozzle (100) as claimed in claim 1, characterized in that, The fuel nozzle (100) further includes a first swirler (301) located upstream of the annular chamber (201) and fluidly connected to the plurality of fuel injection holes (12).

6. The fuel nozzle (100) as claimed in claim 1, characterized in that, The fuel nozzle (100) includes a main combustion stage (101) and a pre-combustion stage (102). The main combustion stage (101) includes the annular chamber (201). At least a portion of the pre-combustion stage (102) is surrounded by the main combustion stage (101). The pre-combustion stage (102) includes an annular body (41) having an outer ring portion (411) that forms the annular inner wall (21) of the annular chamber (201).

7. The fuel nozzle (100) as claimed in claim 6, characterized in that, The pre-combustion stage (102) includes a pre-combustion stage nozzle (42) located on the axis of the annular body (41). The annular body (41) also has an inner ring portion (412) with a second swirler (302) in fluid communication with the pre-combustion stage nozzle (42).

8. The fuel nozzle (100) as claimed in claim 1, characterized in that, It also includes a fuel delivery pipe (5), which is connected to one axial end of the ring body (11) of the fuel ring (1).

9. A combustion chamber (1000) for a gas turbine engine, characterized in that, include: Combustion container; as well as A fuel nozzle (100) as described in any one of claims 1-8 is disposed adjacent to the combustion vessel, the downstream end of the annular chamber (201) of the fuel nozzle (100) being directly connected to the combustion vessel, configured to provide a flow of fuel-air mixture to the combustion vessel.

10. A gas turbine engine, characterized in that, Includes the combustion chamber (1000) as described in claim 9.

11. A method for suppressing oscillating combustion in a gas turbine engine, comprising: A main combustion stage (101) is provided, the main combustion stage (101) being configured as follows: Fuel is injected into the main combustion stage (101) through a plurality of fuel nozzles (12) located thereon. Each plurality of fuel nozzles (12) comprises at least a nozzle group (121, 122, 123, 124) with different axial positions. The nozzle groups (121, 122, 123, 124) are arranged in a ring-like configuration within a ring body (11), forming a plurality of coaxial rings (1210, 1220, 1230, 1240) distributed along the axial direction of the ring body (11). The plurality of coaxial rings (1210, 1220, 1230, 1240) are respectively located at a first axial position (A1), a second axial position (A2), and a third axial position (A3). The first axial position (A1), the second axial position (A2), the third axial position (A3), and the fourth axial position (A4) are distributed at equal intervals in the axial direction. The axial spacing L of the first axial position (A1), the second axial position (A2), the third axial position (A3), and the fourth axial position (A4) satisfies: L / V = T / 8, where V is the velocity of the fuel particles and T is the combustion oscillation period. When oscillating combustion occurs, the nozzle group is selectively formed into at least one combination, and the nozzle groups other than the combination are closed to suppress oscillating combustion.

12. A fuel ring (1) for a fuel turbine engine, characterized in that, The device includes an annular body (11) and a plurality of fuel injection holes (12), which are distributed circumferentially along the annular body (11) and have a radial injection direction. The plurality of fuel injection holes (12) include at least a group of injection holes (121, 122, 123, 124) with different axial positions. These groups of injection holes (121, 122, 123, 124) are arranged in a ring-like configuration within the annular body (11), forming a plurality of coaxial annular rings (1210, 1220, 1230, 1240) distributed axially along the annular body (11). The plurality of coaxial annular rings (1210, 1220, 1230, 1240) are further divided into... The nozzles are located at a first axial position (A1), a second axial position (A2), a third axial position (A3), and a fourth axial position (A4). The first axial position (A1), the second axial position (A2), the third axial position (A3), and the fourth axial position (A4) are distributed at equal intervals in the axial direction. The axial spacing L of the first axial position (A1), the second axial position (A2), the third axial position (A3), and the fourth axial position (A4) satisfies: L / V = T / 8, where V is the velocity of the fuel particles and T is the combustion oscillation period. The nozzle groups (121, 122, 123, 124) can be selectively combined to form at least one combination that suppresses oscillation.

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