CN220648315U - Fuel nozzle, combustion chamber and gas turbine engine - Google Patents

Abstract

The utility model relates to a fuel nozzle, a combustion chamber and a gas turbine engine. The fuel nozzle comprises a nozzle flange, and is used for installing the fuel nozzle to the combustion chamber casing to form a cantilever structure; a nozzle housing and a nozzle head connected to a downstream end of the nozzle housing, the nozzle housing being located radially inward of the nozzle flange; the oil injection rod core comprises an oil injection rod core pipeline and an oil collecting ring part; the oil injection rod core pipeline is arranged in a space surrounded by the nozzle shell; the oil collecting ring part comprises an oil collecting ring, a sleeve and an oil collecting ring supporting part, wherein the oil collecting ring is connected to the sleeve through the oil collecting ring supporting part; wherein the oil collector ring support is a single continuous ring shape in the circumferential direction.

Description

Fuel nozzle, combustion chamber and gas turbine engine

Technical Field

The utility model relates to a fuel nozzle, a combustion chamber and a gas turbine engine.

Background

To achieve low pollution emissions requirements, gas turbine engine combustors typically employ multi-fuel nozzles with staged fuel supply. The fuel nozzle is arranged on the combustion chamber casing, works in high-temperature and high-pressure environments, and vibration excitation load born by the working state mainly comes from pulsating pressure excitation generated by combustion oscillation and vibration excitation of a rotor transmitted by the combustion chamber casing. When the fuel nozzle vibrates, the high-order generation nozzle is internally provided with a fuel injection rod core for local vibration, the high-order vibration orders are more and high in danger, the high-order vibration orders are extremely easy to couple with the combustion oscillation excitation frequency, high-cycle fatigue failure is caused by nozzle resonance, and the safety of an engine is threatened.

In order to meet the design requirements of pneumatic, thermal protection, strength and the like, the design complexity of an oil way and an air way inside the fuel nozzle is high, and the manufacturing of the fuel nozzle with a complex structure can be generally realized through a 3D printing (additive manufacturing) technology. In order to improve the high cycle fatigue life of the fuel nozzle and avoid the resonance risk during the operation of the nozzle, the frequency modulation design needs to be developed, and the nozzle design is highly integrated and difficult, so that a large amount of calculation resources are often consumed, the design period is long, and even the frequency modulation expectation cannot be achieved.

Therefore, there is a need in the art for a fuel nozzle that facilitates a frequency modulation design of the fuel nozzle during a development phase, thereby shortening the development cycle of the fuel nozzle, combustion chamber, gas turbine engine.

Disclosure of Invention

The utility model aims to provide a fuel nozzle.

The utility model also aims to provide a combustion chamber.

It is also an object of the present utility model to provide a gas turbine engine.

The utility model solves the technical problem that the fuel nozzle is easy to carry out frequency modulation design in the research and development stage, thereby shortening the development period of the fuel nozzle, the combustion chamber and the gas turbine engine.

According to a first aspect of the utility model, a fuel nozzle comprises a nozzle flange for mounting the fuel nozzle to a combustor casing to form a cantilever structure;

a nozzle housing located radially inward of the nozzle flange;

the oil injection rod core comprises an oil injection rod core pipeline and an oil collecting ring part; the oil injection rod core pipeline is arranged in a space surrounded by the nozzle shell; the oil collecting ring part comprises an oil collecting ring, a sleeve and an oil collecting ring supporting part, wherein the oil collecting ring is connected with the downstream end of the oil injection rod core pipeline, the sleeve is positioned on the radial inner side of the oil collecting ring, and the oil collecting ring is connected with the sleeve through the oil collecting ring supporting part; a cavity structure is arranged between the oil injection rod core pipeline and the nozzle shell, and gaps are formed among the oil collecting ring, the sleeve, the nozzle shell and the oil collecting ring shell respectively to form an air heat insulation layer; the sleeve provides a hot air passage to isolate the oil collection ring from hot air;

wherein the oil collecting ring support part is in a single continuous ring shape in the circumferential direction, the annular inner wall surface is connected with the outer wall surface of the sleeve, the annular outer wall surface axially extends from the oil collecting ring, and the corresponding central angle of the oil collecting ring support part is 50-200 degrees.

The fuel nozzle described in the above embodiment, by integrating the oil collecting ring support part into a single continuous ring shape in the circumferential direction, the high-order natural frequency of the fuel nozzle can be adjusted by only changing the structure of the single connected partial ring shape in the development process, without considering the interference of other structural factors, so that the fuel nozzle is easy to carry out frequency modulation design of the fuel nozzle in the development stage, and the development period of the fuel nozzle, the combustion chamber and the gas turbine engine is shortened.

In one or more embodiments of the fuel nozzle, the outer wall surface of the oil collector ring support is perforated.

In one or more embodiments of the fuel nozzle, the annular oil collector support portion extends symmetrically upward from the bottom of the oil collector on both sides in the circumferential direction.

In one or more embodiments of the fuel nozzle, the annular oil collector support portion extends asymmetrically upward from the bottom of the oil collector on both sides in the circumferential direction, and extends shorter on the side of the oil collector where the pre-combustion stage oil passage is connected.

In one or more embodiments of the fuel nozzle, the fuel injection stem core is an additively manufactured integral piece.

In one or more embodiments of the fuel nozzle, the sleeve is connected to the nozzle housing and the oil collection ring housing, respectively, by a welded structure.

In one or more embodiments of the fuel nozzle, the nozzle housing and the oil collector ring housing are connected by a welded structure.

According to a second aspect of the utility model, a combustion chamber comprises the fuel nozzle as described in the first aspect, a flame tube and a casing, wherein fuel output of the fuel nozzle burns on the flame tube, and the fuel nozzle is fixed on the casing through a nozzle flange.

In one or more embodiments of the combustion chamber, the flame tube comprises a flame tube outer ring, a flame tube inner ring, the casing comprises a combustion chamber outer casing, a combustion chamber inner casing, and air entering the combustion chamber is provided with the following flow paths: the first flow path enters a flame tube inner cavity defined by the flame tube outer ring and the flame tube inner ring through the fuel nozzle head and is subjected to combustion reaction with fuel injected by the fuel nozzle; a second flow path flowing to a liner outer ring cavity defined by the liner outer ring and the combustion chamber outer casing; and a third flow path flowing to a liner inner ring cavity defined by the liner inner ring and the combustion chamber casing.

The advantage of the combustion chamber described above is that the development cycle of the combustion chamber can be shortened by including the fuel nozzle of the first aspect.

A gas turbine engine according to a third aspect of the utility model comprises a combustion chamber as in the second aspect, and a compressor that provides air to the combustion chamber for combustion.

The gas turbine engine described above has the advantage that the development cycle of the gas turbine engine can be shortened by including the combustion chamber of the second aspect.

Drawings

The above and other features, properties and advantages of the present utility model will become more apparent from the following description in conjunction with the accompanying drawings and embodiments, in which:

FIG. 1 is a schematic structural view of a combustion chamber of a gas turbine engine of an embodiment.

Fig. 2A and fig. 2B are schematic structural diagrams of a fuel nozzle according to an embodiment.

Fig. 3A and 3B are schematic diagrams illustrating a structure of a fuel nozzle according to an embodiment.

Fig. 4A and 4B are schematic diagrams illustrating another structure of the fuel nozzle according to an embodiment.

Fig. 5A and 5B are schematic diagrams illustrating another structure of a fuel nozzle according to an embodiment.

Detailed Description

The present utility model will be further described with reference to specific embodiments and drawings, in which more details are set forth in the following description in order to provide a thorough understanding of the present utility model, but it will be apparent that the present utility model can be embodied in many other forms than described herein, and that those skilled in the art may make similar generalizations and deductions depending on the actual application without departing from the spirit of the present utility model, and therefore should not be construed to limit the scope of the present utility model in terms of the content of this specific embodiment.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application; the terms "comprising" and "having" and any variations thereof in the description and claims of the present application and in the description of the figures above are intended to cover non-exclusive inclusions.

Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the present application. The appearances of such phrases in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. Those of skill in the art will explicitly and implicitly appreciate that the embodiments described herein may be combined with other embodiments.

In the description of the embodiments of the present application, the orientation or positional relationship indicated by the technical terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. are based on the orientation or positional relationship shown in the drawings, and are merely for convenience of describing the embodiments of the present application and for simplifying the description, rather than indicating or implying that the apparatus or element referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the embodiments of the present application.

In the description of the embodiments of the present application, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured" and the like are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally formed; but also mechanical connection, and the specific meaning of the above terms in the embodiments of the present application will be understood by those skilled in the art according to the specific circumstances.

The application scenario of the fuel nozzle disclosed in the embodiment of the application is exemplified by a gas turbine engine as an aeroengine. However, the present utility model is not limited thereto, and may be applied to other cases using a gas turbine engine, such as a marine gas turbine engine, as long as the problem of vibration fatigue life of the fuel nozzle is present, and the present utility model is applicable to the fuel nozzle and the combustion chamber to shorten the development cycle.

As shown in fig. 1, a combustion chamber 1000 of a gas turbine engine may include a combustion chamber housing 101, a diffuser 201, a combustion chamber housing 301, a liner outer ring 401, a liner inner ring 501, fuel nozzles 601, a fuel nozzle head 602. Air is pressurized by a compressor of a gas turbine engine, typically a high-pressure compressor to form a high-pressure compressor outlet airflow 701, the air is diffused by a diffuser 201 to flow, the pressure is increased, and the air enters a combustion chamber and is generally divided into three air flow paths: one is nozzle head air inlet 702 for forming rotational flow with fuel, and the other two is flame tube outer ring cavity air inlet 703 and flame tube inner ring cavity air inlet 704 for cooling the flame tube. That is, the nozzle tip inlet air 702 is a first flow path, and enters the inner cavity 705 of the flame tube defined by the outer ring 401 and the inner ring 501 of the flame tube from the fuel nozzle tip 602, and is combusted with the fuel injected by the fuel nozzle 601. Specifically, for a concentric staged combustion chamber configuration, it is possible that the nozzle tip inlet air 702 splits into two streams, one stream passing through the air flow passage defined by sleeve 609, through the nozzle secondary swirler, and blending with the pre-stage fuel; the other is the air flow passage defined by the oil collector housing 607, through the nozzle primary swirler, for blending with the primary fuel.

The liner outer ring cavity intake 703 is a second flow path, air flows to the liner outer ring cavity defined by the liner outer ring 401 and the combustion chamber outer casing 101, the liner inner ring cavity intake 704 is a third flow path, and air flows to the liner inner ring cavity defined by the liner inner ring 501 and the combustion chamber inner casing 301. The fuel nozzle 601 can be fixed on the combustion chamber outer casing 101 through a nozzle flange 604 and a bolt connection, and works in a high-temperature and high-pressure environment, wherein the high pressure is generated by the air flow of a high-pressure compressor and the fuel oil in the nozzle, and the high temperature is generated by the heating of the air flow of the outlet of the compressor and the heat convection and heat radiation of the nozzle by the high-temperature combustion environment in the inner cavity 705 of the flame tube. The fuel nozzle is manufactured by using a high-temperature alloy to cope with the severe working environment of high temperature and high pressure. When the fuel nozzle works, the combustion oscillation excitation load is derived from combustion pulsation pressure generated by the inner cavity 705 of the flame tube, the pulsation pressure acts on the fuel nozzle through the nozzle head 602, and the rotor vibration excitation is transmitted to the nozzle flange 604 through the combustion chamber outer casing 101 and further transmitted to the fuel nozzle 601. In addition, the mechanical properties of the material are reduced in a high-temperature environment, and the nozzle is more prone to high-cycle fatigue failure, so that the nozzle faces a serious challenge of thermal vibration fatigue. The fuel nozzle head 602, which may also be referred to generally herein as a combustion chamber head, includes, for example, structures forming a main combustion stage, a pre-combustion stage, and a corresponding swirler.

As shown in fig. 2A and 2B, the fuel nozzle 601 includes a nozzle flange 604, a nozzle housing 605, and a fuel rod core. The oil injection rod core is internally provided with a plurality of fuel oil flow paths, so that the oil injection rod core can be manufactured into an integral molding part through an additive manufacturing process, and the manufacturing of a complex structure is realized. The nozzle flange 604 is used to mount the fuel nozzle 601 to the combustor casing, forming a cantilever structure. Cantilever structure is herein understood to mean a similar structure in mechanics in which the vibration of the cantilever beam is stressed. The nozzle housing 605 is located radially inward of the nozzle flange 604. The fuel injector stem insert includes a fuel injector stem insert conduit 606 and a fuel collector ring portion; wherein the fuel injection stem core pipe 606 is disposed in the space surrounded by the nozzle housing 605; the oil collecting ring portion includes an oil collecting ring 608, a sleeve 609, and an oil collecting ring support portion 610, the oil collecting ring 608 is connected to a downstream end of the oil injection rod core pipe 606, the sleeve 609 is located radially inward of the oil collecting ring 608, and the oil collecting ring 608 is connected to the sleeve 609 through the oil collecting ring support portion 610. The oil catcher support 610 is located in the small space within the nozzle formed by the fuel nozzle housing 605 and sleeve 609 and serves to connect the oil catcher 608 and sleeve 609 to form a transitional structure. Preferably, the sleeve 609 is connected with the nozzle housing 605 and the oil collecting ring housing 607 respectively through a first welding structure 6031 and a second welding structure 6032, namely, the sleeve 609 is sleeved on the nozzle housing 605 and connected through welding; the nozzle housing 605 and the oil collector housing 607 are connected by a third weld 6033. The specific form of the welded structure may be a brazed welded structure, but is not limited thereto. After passing through the fuel injection rod core pipe 606 and the oil collecting ring 608 of the fuel injection rod core through the valve mounting seat 603, fuel is atomized at the nozzle head 602 and mixed with the air intake 702 of the nozzle head to enter the inner cavity 705 of the flame tube for combustion.

The oil rod core tube 606 is shown as being approximately a straight-through tube at both ends, while the oil collection ring 608 also provides fuel flow, the oil collection ring 608 is also referred to as being of annular configuration, as shown, the oil collection ring is simplified in terms of simple annular configuration, but not limited thereto, for example the oil collection ring 608 may be generally annular in shape, but the tube extends in a serpentine manner. In general, in the fuel nozzle, a plurality of oil holes distributed in the circumferential direction are provided in the oil collecting ring 608, and supply oil to the main fuel stage of the nozzle head. After extending to its downstream end, the fuel rod core tube 606 extends axially a length and connects to the top end of the oil collection ring 608. Since the fuel rod core tube 606 and the oil catcher ring portion are generally integrally formed, both are generally designated as fuel rod cores in their entirety. A cavity structure 6010 exists between the fuel rod core tube 606 and the nozzle housing 605. The oil collecting ring 608 is respectively provided with a gap 6020 with the nozzle housing 605, the oil collecting ring housing 607 and the sleeve 609 to form an air heat insulation layer; sleeve 609 provides a hot air passage to isolate oil collection ring 608 from the hot air. This has the advantage that the nozzle housing 605, oil collector housing 607 and sleeve 609 are heated at a higher temperature by the high temperature air flow at the compressor outlet, while the oil lance core tube 606 is kept at a lower temperature to inhibit coking of the fuel. Because of the existence of the cavity and the gap, high-order vibration of the nozzle is easy to occur to the oil injection rod core in the nozzle, the main vibration mode is the local vibration mode of the oil collecting ring 608, the natural frequency of vibration is high, the oil injection rod core is easy to couple with the combustion oscillation excitation frequency, and the high-cycle fatigue damage risk of the nozzle is high. Therefore, during the development design phase, a frequency modulation design of the fuel nozzle 601 is required.

The specific frequency modulation design step can be that the fuel nozzle is arranged on the combustion chamber casing, and the fuel nozzle works in a high-temperature and high-pressure environment, and vibration excitation load born by the working state mainly comes from pulsation pressure excitation generated by combustion oscillation and rotor vibration excitation transmitted by the combustion chamber casing. First, finite element modeling of the fuel nozzle is carried out, and high-order natural frequencies of the nozzle are obtained through modal analysis. From the nozzle excitation frequency and the natural frequency, the frequency margin thereof is calculated as shown in formula (1). The frequency margin is used for measuring the approaching degree of the natural frequency and the working excitation frequency of the nozzle, and when the nozzle is designed in a vibrating way, the frequency margin needs to meet the criterion requirement, such as 10% or 20%, and a certain resonance margin is required for the nozzle, so that the working state of the nozzle is ensured not to generate resonance. If the nozzle resonance margin does not meet the criterion requirement, the nozzle frequency modulation design is required to be carried out, and the iteration of the steps is carried out again after frequency modulation until the nozzle resonance margin meets the criterion requirement.

Wherein, gamma is the frequency margin; f (f) _e The excitation frequency is, for example, 1E-4E rotor excitation frequency and combustion oscillation excitation frequency; f (f) _n Is the natural frequency of the fuel nozzle.

With continued reference to fig. 2A and 2B, and in combination with fig. 3A, 3B, 5A and 5B, the oil collector support 610 is circumferentially a single continuous ring with an annular inner wall surface connecting the outer wall surface of the sleeve 609, the annular outer wall surface extending axially from the oil collector 608, the oil collector support 610 corresponding to a central angle of 50 ° -200 °.

The oil collecting ring support 610 is integrated into a single continuous partial ring shape in the circumferential direction, so that the high-order natural frequency of the fuel nozzle can be adjusted by only changing the structure of the single connected partial ring shape in the research and development process without considering the interference of other structural factors, the fuel nozzle is easy to carry out frequency modulation design of the fuel nozzle in the research and development stage, and the development period of the fuel nozzle, a combustion chamber and a gas turbine engine is shortened. In addition, since the central angle of the oil collecting ring supporting portion 610 is set to be 50 ° -200 °, the oil collecting ring supporting portion 610 can not only realize stable supporting of the oil collecting ring 608, but also prevent stress caused by different heated conditions on two sides of the oil collecting ring supporting portion 610 from influencing structural stability due to overlarge central angle, and the principle is that the oil collecting ring supporting portion 610 has lower temperature due to the existence of fuel flow by connecting the sleeve 609 with the oil collecting ring 608, and the sleeve 609 provides an air flow path of high-temperature air entering the combustion chamber 1000 to the fuel nozzle head 602, so that the temperature of the sleeve 609 is higher, the oil collecting ring supporting portion 610 can cause certain extrusion stress due to uneven heating on two sides due to different temperatures of connected components, and the inventor finds that if the central angle corresponding to the oil collecting ring supporting portion 610 is too large, the stress caused by uneven heating can have hidden trouble that influences the fatigue life of the oil collecting ring supporting portion 610.

Referring to fig. 3A and 3B, in some embodiments, an annular oil collector support 610 extends symmetrically upward from the bottom of the oil collector 608 along both sides in the circumferential direction. However, for example, the extension may be asymmetric, and the extension may be shorter on the side where the oil collecting ring 608 is connected to the pre-combustion oil passage, as shown in fig. 3A and 3B, and the extension length of the oil collecting ring support portion 610 from the bottom of the oil collecting ring 608 to the left side along the circumferential direction may be longer, and the extension length of the right side may be shorter, so that the natural frequency adjustment range of the core may be wider.

With continued reference to fig. 3A-5B, for higher order natural frequency tuning of the fuel nozzle, the tuning of the tuning design to the oil catcher support 610 may be as shown in fig. 3A and 3B:

oil catcher support 610 is positioned at the bottom of oil catcher 608 to provide for tuning of oil spray bar wick 606 by adjusting the angle of its corresponding central angle. As shown, the oil collecting ring support 610 initially corresponds to the central angle B1, and if the central angle B1 is increased to the central angle B2, the connection rigidity between the oil collecting ring support 610 and the oil collecting ring 608 can be increased, so that the natural frequency of the oil injection rod core can be improved. Conversely, if the corresponding central angle of oil catcher support 610 is reduced, the natural frequency of oil boom core 606 may be reduced. The frequency modulation design of the central angle corresponding to the oil collecting ring support 610 is adjusted, the pneumatic layout and the oil path structure of the fuel nozzle are not changed, the normal operation of the nozzle is not affected, the natural frequency of the oil injection rod core can be adjusted to be high and low, the frequency modulation range is wide, and the frequency modulation effect is obvious.

For higher order natural frequency tuning of the fuel nozzle, tuning of the tuning design to the oil catcher support portion 610 may also be as described with reference to fig. 4A and 4B:

adjusting the thickness of the oil catcher support 610 may enable adjustment of the natural frequency of the oil rod wick, i.e., the higher order natural frequency of the fuel nozzle. If the initial thickness of the oil catcher support 610 is C1 in fig. 4A, and the support thickness is increased to C2 in fig. 4B, the connection stiffness of the oil catcher support 610 and the oil catcher 608 can be increased, thereby increasing the high-order natural frequency of the fuel nozzle. Conversely, if the thickness of the fm support is reduced, the higher order natural frequency of the fuel nozzle may be reduced. However, the reduction in thickness of the oil catcher support 610 is limited, and the sleeve 609 to which the oil catcher support is connected has a high temperature, the oil catcher 608 has a low temperature, the temperature gradient on the support is large, and the thermal stress is high; in addition, when the oil injection rod core vibrates, high vibration stress is also positioned on the radian inverted circle of the middle section of the oil collecting ring support 610, dynamic and static stress is superposed on the support, and the supporting thickness of the oil collecting ring is required to meet the strength design requirement.

For higher order natural frequency tuning of the fuel nozzle, tuning of the tuning design to the oil catcher support portion 610 may also be as described with reference to fig. 5A and 5B:

by providing holes 611 in the outer wall surface of oil catcher support 610, tuning of oil boom core 606 may be accomplished. The oil collecting ring supporting initial structure as in fig. 5A does not contain the hole 611, and by opening the hole 611 as shown in fig. 5B on the outer wall surface, the supporting rigidity can be reduced, thereby reducing the high-order natural frequency of the fuel nozzle, and thus the hole 611 can also be called a frequency modulation hole. The number, arrangement and hole pattern of the holes can be designed according to the frequency modulation requirement so as to meet the requirement of the design frequency margin of the high-order natural frequency and the excitation frequency of the fuel nozzle. In addition, the support stiffness can be changed by changing the cross-sectional shape or configuration of the oil collection ring support 610, thereby achieving the oil spray rod core frequency modulation.

In summary, the beneficial effects of the fuel nozzle, the combustion chamber and the gas turbine engine described in the above embodiments include, but are not limited to, by integrating the oil collecting ring support part into a single continuous ring shape in the circumferential direction, so that the high-order natural frequency of the fuel nozzle can be adjusted by only changing the structure of the single connected partial ring shape in the development process, without considering the interference of other structural factors, and the fuel nozzle is easy to perform frequency modulation design of the fuel nozzle in the development stage, thereby shortening the development period of the fuel nozzle, the combustion chamber and the gas turbine engine.

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

Claims (10)

1. A fuel nozzle (601), characterized by comprising:

a nozzle flange (604) for mounting the fuel nozzle (601) to a combustor casing to form a cantilever structure;

a nozzle housing (605) located radially inward of the nozzle flange (604);

the oil injection rod core comprises an oil injection rod core pipeline and an oil collecting ring part; wherein the oil injection rod core pipe (606) is arranged in a space surrounded by the nozzle shell (605); the oil collecting ring part comprises an oil collecting ring (608), a sleeve (609) and an oil collecting ring supporting part (610), wherein the oil collecting ring (608) is connected with the downstream end of the oil injection rod core pipe (606), the sleeve (609) is positioned on the radial inner side of the oil collecting ring (608), and the oil collecting ring (608) is connected with the sleeve (609) through the oil collecting ring supporting part (610); a cavity structure (6010) is arranged between the oil injection rod core pipeline (606) and the nozzle housing (605), and gaps (6020) are formed among the oil collecting rings (608), the nozzle housing (605), the oil collecting ring housing (607) and the sleeve (609) respectively to form an air heat insulation layer; the sleeve (609) provides a hot air channel to isolate the oil collection ring (608) from hot air;

wherein the oil collecting ring support (610) is in a single continuous ring shape in the circumferential direction, an annular inner wall surface is connected with an outer wall surface of the sleeve (609), the annular outer wall surface extends axially from the oil collecting ring (608), and a corresponding central angle of the oil collecting ring support (610) is 50-200 degrees.

2. The fuel nozzle (601) according to claim 1, wherein the outer wall surface of the oil collecting ring support (610) is provided with a hole (611).

3. The fuel nozzle (601) according to claim 1, characterized in that the annular oil collecting ring support (610) extends symmetrically upward from the bottom of the oil collecting ring (608) along both sides in the circumferential direction.

4. The fuel nozzle (601) according to claim 1, characterized in that the annular oil collecting ring support (610) extends asymmetrically upward from the bottom of the oil collecting ring (608) along both sides in the circumferential direction, and extends shorter on the side of the oil collecting ring (608) where the pre-combustion stage oil passage is connected.

5. The fuel nozzle (601) according to claim 1, wherein the fuel rod core is an additively manufactured integral piece.

6. The fuel nozzle (601) according to claim 1, characterized in that the sleeve (609) is connected to the nozzle housing (605) and the oil-collecting ring housing (607) by means of welded structures, respectively.

7. The fuel nozzle (601) according to claim 6, wherein the nozzle housing (605) and the oil-collecting ring housing (607) are connected by a welded structure.

8. A combustion chamber (1000) comprising a flame tube, a casing and a fuel nozzle (601) according to any of claims 1-7, wherein a fuel output of the fuel nozzle (601) is combusted in the flame tube, and wherein the fuel nozzle (601) is secured to the casing by means of the nozzle flange (604).

9. The combustor (1000) of claim 8, wherein the liner comprises a liner outer ring (401), a liner inner ring (501), the casing comprises a combustion chamber outer casing (101), a combustion chamber inner casing (301), and air entering the combustor (1000) is provided with the following flow paths:

a first flow path enters a flame tube inner cavity (705) defined by a flame tube outer ring (401) and a flame tube inner ring (501) through a fuel nozzle head (602) and is subjected to combustion reaction with fuel injected by the fuel nozzle (601);

a second flow path flowing to a liner outer ring cavity defined by the liner outer ring (401) and the combustion chamber outer casing (101);

and a third flow path flowing to a liner inner ring cavity defined by the liner inner ring (501) and the combustion chamber inner casing (301).

10. A gas turbine engine comprising a compressor and a combustion chamber (1000) according to claim 8 or 9, said compressor providing air to said combustion chamber (1000) for combustion.