Ignition electrode and aeroengine

Abstract

The application provides an ignition electrode and an aero-engine. The ignition electrode comprises a body, the body has an axially arranged mounting portion and a discharge portion, the mounting portion is detachably connected with a casing, the discharge portion is clamped on a flame tube through a floating mounting piece and extends towards the inside of the flame tube at one end, at least one cooling groove is formed on the outer circumferential side of the discharge portion along the axial direction, one side port of the cooling groove is communicated with a cavity between the casing and the flame tube, the other side port of the cooling groove is communicated with the inner cavity of the flame tube, and the cross-sectional dimension of the cooling groove decreases in the direction from the mounting portion to the flame tube. The ignition electrode of the application has at least one cooling groove formed on the outer circumferential side of the discharge portion along the axial direction, and the cross-sectional dimension of the cooling groove decreases in the direction from the mounting portion to the flame tube. Thus, when the ignition electrode is in different extension amounts, the flame tube side has different amounts of cooling gas, the greater the extension amount, the greater the amount of cooling gas, and the maximum utilization of the cooling gas is realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of ignition electrode cooling, in particular to an ignition electrode and an aero-engine. BACKGROUND

[0002] In an aero-engine, the combustion chamber is the area where combustion is organized. The compressed air from the compressor enters the combustion chamber and mixes with the fuel gas sprayed by the fuel nozzle, and then burns to produce high-temperature fuel gas to drive the turbine to work and generate thrust. In the combustion chamber, the oil-gas mixture is ignited by the energy generated by the ignition electrode.

[0003] The ignition electrode is generally installed on the combustion chamber case and extends into the flame tube through a hole in the combustion chamber case. The flame tube is the combustion area of the combustion chamber, that is, the oil-gas mixing area. The ignition electrode generally needs to be flush with the inner wall of the flame tube. If the extension amount is not enough, it will affect the ignition success rate. If the extension amount is too large, it will cause ablation problems at the end of the electrode.

[0004] The flame tube is a thin-walled part. The installation depth of the ignition electrode cannot be controlled due to the assembly or deformation of the flame tube itself. In the transient process of the engine, the temperature of the flame tube is high, the wall is thin, and the temperature rises quickly. The temperature of the case is low, the wall is thick, and the temperature response is slow. In the transient state, the electrode protrudes from the surface of the flame tube and causes ablation problems.

[0005] At present, various types of engines use the method of opening an air guide groove on the ignition electrode to achieve end cooling of the ignition electrode. However, the rectangular through groove often causes the airflow to directly blow into the combustion area, and the air volume is small. The cooling effect of the slotted interval position at the end of the ignition electrode is poor, which causes ablation. If the air volume is increased, the actual air volume used by the engine in the combustion chamber will be reduced, which will reduce the combustion performance. Moreover, the middle of the end of the ignition electrode has no cooling air supply, so it is also a serious area of ablation.

[0006] Therefore, the present application provides an ignition electrode and an aero-engine to solve the above technical problems. SUMMARY

[0007] The technical problem to be solved by the present application is to overcome the defect that the cooling groove cannot control the cooling air volume of the ignition electrode in different states in the prior art, and to provide an ignition electrode and an aero-engine.

[0008] The present application solves the above technical problems by the following technical scheme:

[0009] The present application provides an ignition electrode, which is characterized by comprising:

[0010] The body has an axially arranged mounting portion and a discharge portion, the mounting portion is detachably connected with the case, and the discharge portion is clamped on the flame tube by a floating mounting member and extends towards the inside of the flame tube at one end;

[0011] At least one cooling groove is formed on the outer periphery of the discharge portion along the axial direction, one side port of the cooling groove is communicated with the cavity between the case and the flame tube, and the other side port of the cooling groove is communicated with the inner cavity of the flame tube; wherein,

[0012] The cross-sectional dimension of the cooling groove decreases in the direction from the mounting portion to the flame tube.

[0013] According to one embodiment of the present application, a gas guide channel is arranged on the floating mounting member, and the discharge portion penetrates the gas guide channel;

[0014] The cooling groove is communicated with the gas guide channel, at least one cooling hole is formed on the floating mounting member, one side port of the cooling hole is communicated with the cavity between the case and the flame tube, and the other side port of the cooling hole is communicated with the inner cavity of the flame tube.

[0015] According to one embodiment of the present application, the angle between the hole diameter of the cooling hole and the axis of the discharge portion is arranged.

[0016] According to one embodiment of the present application, the floating mounting member includes a floating sleeve, a cover plate arranged outside the floating sleeve, and a mounting seat connected with the cover plate, one end of the mounting seat is connected with the flame tube;

[0017] The cooling hole is formed on the floating sleeve, and a plurality of cooling holes are arranged at intervals around the outer periphery of the floating sleeve.

[0018] According to one embodiment of the present application, a mounting hole is formed on the cover plate, one end of the floating sleeve penetrates the mounting hole and is clamped in the mounting gap between the cover plate and the mounting seat, the other end of the floating sleeve is designed as a flared portion and has a collection cavity, and the collection cavity is communicated with the cooling groove.

[0019] According to one embodiment of the present application, the mounting seat forms a flow collection cavity with the discharge portion and the flame tube, and the circumferential cross-sectional dimension of the flow collection cavity is greater than the circumferential dimension of the discharge portion;

[0020] The flow collection cavity, the collection cavity and the cooling groove jointly constitute the gas guide channel.

[0021] According to one embodiment of the present application, the end portion of the discharge portion away from the mounting portion is designed as a closed end.

[0022] According to one embodiment of the present application, a plurality of cooling grooves are uniformly and circumferentially arranged around the outer periphery of the discharge portion.

[0023] According to one embodiment of the present application, the mounting portion is detachably connected with the casing through screw threads.

[0024] The present application also provides an aero-engine, characterized in comprising:

[0025] A flame tube;

[0026] A casing;

[0027] The ignition electrode as described above is connected with the flame tube and the casing respectively.

[0028] The positive progress effect of the present application is that:

[0029] The ignition electrode of the present application is provided with at least one cooling groove along the axial direction of the outer peripheral side of the discharge portion, and the cross-sectional size of the cooling groove decreases in the direction from the mounting portion to the flame tube, so that when the ignition electrode is in different extension amounts, the flame tube side has different cooling gas amounts, and the greater the extension amount, the greater the cooling gas amount, thereby realizing the maximum utilization of the cooling gas.

[0030] The end portion of the discharge portion away from the mounting portion is designed to be closed, so as to realize the dispersion and coverage of the cooling gas on the cylindrical end face of the ignition electrode, and form an isolation cavity in the center of the outlet end portion of the ignition electrode, so as to achieve the effect of blocking high-temperature combustion gas and cooling the center of the end portion of the ignition electrode. BRIEF DESCRIPTION OF DRAWINGS

[0031] The above and other features, properties, and advantages of the present application will become more apparent by the following description with reference to the accompanying drawings and embodiments, in which:

[0032] Figure 1 Part structure diagram of the aero-engine of the present application;

[0033] Figure 2 Structure diagram of the body of the ignition nozzle of the present application;

[0034] Figure 3 Cross-sectional view of a state of the ignition nozzle in Figure 1

[0035] Cross-sectional view of another state of the ignition nozzle in Figure 4 Figure 1

[0036] 10, body;

[0037] 20, mounting portion;

[0038] 30, discharge portion; 310, cooling groove;

[0039] ​​40, floating mounting; 410, air guide channel; 420, cooling hole; 430, floating sleeve; 431, collecting cavity; 440, cover plate; 441, mounting hole; 450, mounting seat; 460, converging cavity;

[0040] 50, flame tube;

[0041] 60, case;

[0042] 70, ignition electrode. DETAILED DESCRIPTION

[0043] In order to make the above objectives, characteristics and advantages of the present application more apparent, the specific embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0044] Reference will now be made in detail to the embodiments of the present application, examples of which are illustrated in the accompanying drawings. Wherever possible, the same reference numbers will be used throughout the drawings to refer to the same or like parts. In addition, although the terms used in the present application are selected from generally known and used terms, some of the terms mentioned in the description of the present application can be selected by the applicant in his or her judgment, and the detailed meanings thereof are described in relevant parts of the description. Furthermore, the present application should not be understood to be limited only to the actual terms used but also to also the meanings of each term underlying the terms.

[0045] Reference will now be made in detail to the embodiments of the present application, examples of which are illustrated in the accompanying drawings. Wherever possible, the same reference numbers will be used throughout the drawings to refer to the same or like parts. In addition, although the terms used in the present application are selected from generally known and used terms, some of the terms mentioned in the description of the present application can be selected by the applicant in his or her judgment, and the detailed meanings thereof are described in relevant parts of the description. Furthermore, the present application should not be understood to be limited only to the actual terms used but also to also the meanings of each term underlying the terms. Figures 1 to 4 The present application proposes an ignition electrode 70, which includes a body 10 having an axially arranged mounting portion 20 and a discharge portion 30, the mounting portion 20 is detachably connected with a case 60, and the discharge portion 30 is clamped to a flame tube 50 by a floating mounting 40 and extends toward the inside of the flame tube 50. The mounting portion 20 and the discharge portion 30 can be integrally arranged, or can be fixedly connected by adhesion or welding, or can be connected by a threaded connection, which is not limited herein.

[0046] In one embodiment, the mounting portion 20 and the case 60 can be detachably connected by welding, adhesion or a threaded connection. Preferably, the mounting portion 20 and the case 60 are detachably connected by a threaded connection, which facilitates the maintenance and replacement of the ignition electrode 70. In some other embodiments, other connection methods can be used, which are not limited herein.

[0047] Specifically, at least one cooling groove 310 is formed on the outer circumferential side of the discharge portion 30 along the axial direction thereof, one side port of the cooling groove 310 is in communication with a cavity between the case 60 and the flame tube 50, and the other side port of the cooling groove 310 is in communication with the inner cavity of the flame tube 50. The cross-sectional dimension of the cooling groove 310 decreases in the direction from the mounting portion 20 to the flame tube 50.

[0048] The flow passage between the casing 60 and the flame tube 50 is a cooling gas passage, and the cooling gas in the flow passage is used to enter the end of the discharge portion 30 through the flow passage and the cooling groove 310, and then cool the end of the discharge portion 30 to avoid burning of the surface of the discharge portion 30 at high temperature during ignition.

[0049] That is, the opposite ends of the cooling groove 310 need to be communicated with the flow passage and the inner cavity of the flame tube 50, so that the end of the discharge portion 30 of the ignition electrode 70 is cooled by the cooling gas on the side of the flow passage.

[0050] It should be noted that the amount of cooling gas required for different working conditions is inconsistent, and the traditional scheme also has a structure of the cooling groove 310, but the shape of the traditional cooling groove 310 is mostly a rectangular groove penetrating the body 10. The cooling gas sweeps the outside of the discharge portion 30 and is directly blown into the inner cavity of the flame tube 50. The cooling gas stays on the outer peripheral side of the discharge portion 30 for a very short time, so that the amount of cooling gas received by the discharge portion 30 is very small, and the cooling effect is poor. If the amount of gas is increased to increase the amount of cooling gas of the discharge portion 30, the actual amount of gas used by the engine for the combustion chamber will be reduced, which will further reduce the combustion performance.

[0051] Please refer to Figure 2 The present application sets the cross-sectional dimension of the cooling groove 310 along the direction from the mounting portion 20 to the flame tube 50 in a decreasing manner, adopts a variable cross-section non-straight-through type cooling groove 310 structure, so that the cooling gas is not directly blown into the inner cavity of the flame tube 50, but breaks the flow direction of the cooling gas, so that more cooling gas stays in the space on the outer peripheral side of the discharge portion 30. This setting method can avoid the gas from being rolled into the flow passage, and can improve the cooling efficiency on the peripheral side of the discharge portion 30.

[0052] In one embodiment, the floating mounting member 40 is provided with a gas guide passage 410, the discharge portion 30 penetrates the gas guide passage 410, the cooling groove 310 is communicated with the gas guide passage 410, and at least one cooling hole 420 is formed in the floating mounting member 40. One side port of the cooling hole 420 is communicated with the cavity between the casing 60 and the flame tube 50, and the other side port of the cooling hole 420 is communicated with the inner cavity of the flame tube 50.

[0053] The cooling hole 420 is used to continuously input cooling gas to the peripheral side of the discharge portion 30, and the cooling gas introduced through the cooling hole 420 and the cooling groove 310 converges on the peripheral side of the discharge portion 30 and forms a gas film on the peripheral side of the discharge portion 30, so that the end of the discharge portion 30 is not ablated during ignition.

[0054] Specifically refer to Figure 1The aero-engine comprises a compressor, a combustion chamber and a turbine, the compressed airflow is reduced in speed by an expander, enters the flame tube 50, mixes with the fuel sprayed by the fuel nozzle, and is ignited by the high-energy spark generated by the ignition electrode 70 to realize combustion.

[0055] The ignition electrode 70 is installed on the combustion chamber case 60 and penetrates into the flame tube 50, the end surface of the ignition electrode 70 should be flush with the inner wall surface of the flame tube 50 or within a certain range to ensure efficient ignition and not be ablated.

[0056] In an embodiment, the angle between the hole diameter of the cooling hole 420 and the axis of the discharge part 30 is set.

[0057] In this way, the cooling gas flowing out of the cooling hole 420 and the cooling gas flowing out of the cooling groove 310 also have an angle, and when the two gas flows of the cooling hole 420 and the cooling groove 310 converge, the original cooling groove 310 gas flow is dispersed by the cooling hole 420 gas flow, avoiding the cooling gas directly entering the flame tube 50, and increasing the residence time of the cooling gas on the periphery of the discharge part 30, thereby improving the cooling effect on the periphery of the discharge part 30.

[0058] In an embodiment, the floating mounting 40 comprises a floating sleeve 430, a cover plate 440 sleeved outside the floating sleeve 430, and a mounting seat 450 connected with the cover plate 440, one end of the mounting seat 450 is connected with the flame tube 50, the cooling hole 420 is opened on the floating sleeve 430, and a plurality of cooling holes 420 are arranged at intervals around the outer periphery of the floating sleeve 430.

[0059] The mounting seat 450 and the flame tube 50 can be connected by bonding or welding. In an embodiment of the present application, the mounting seat 450 and the flame tube 50 are preferably welded, and the mounting seat 450 and the cover plate 440 are used to cooperate with the floating sleeve 430.

[0060] In an embodiment, the cover plate 440 is provided with a mounting hole 441, one end of the floating sleeve 430 is inserted into the mounting hole 441 and clamped in the mounting gap between the cover plate 440 and the mounting seat 450, and the other end of the floating sleeve 430 is designed as a flared structure and has a collection cavity 431, the collection cavity 431 is in communication with the cooling groove 310.

[0061] The flared end of the floating sleeve 430 is similar to a bell mouth structure, which is configured to collect more cooling air flow into the cooling groove 310. The mounting hole 441 on the cover plate 440 is at least larger than the circumferential dimension of the floating sleeve 430 at the mounting position, and the cooling hole 420 is in communication with the gap between the mounting hole 441 and the floating sleeve 430 at one end, and faces the discharge portion 30 at the other end. The air inlet side of the cooling hole 420 flows into the mounting hole 441, and flows out towards the outer peripheral side of the discharge portion 30, so as to be combined with the cooling air flow of the cooling groove 310, and the collected cooling air forms an air film on the outer peripheral side of the discharge portion 30 to avoid the influence of high temperature.

[0062] In some other embodiments, the cooling hole 420 can also be directly provided in the cover plate 440 and the floating sleeve 430, so that the cooling air enters the cooling hole 420 through the space outside the cover plate 440, and then flows to the outer peripheral side of the discharge portion 30 after flowing through the cooling hole 420. The specific arrangement of the cooling hole 420 is not limited here. As long as the cooling hole 420 can guide the cooling air to the discharge portion 30.

[0063] The angle between the diameter direction of the cooling hole 420 and the axial direction of the discharge portion 30 is preferably an acute angle, so that the cooling air in the cooling hole 420 and the cooling groove 310 is combined with the high-temperature gas in the inner cavity of the flame tube 50 to form a head-on collision, avoiding the high-temperature gas in the flame tube 50 from entering the chamber between the casing 60 and the flame tube 50.

[0064] Further, the mounting seat 450 forms a confluence cavity 460 between the discharge portion 30 and the flame tube 50, and the circumferential cross-sectional dimension of the confluence cavity 460 is greater than the circumferential dimension of the discharge portion 30. The confluence cavity 460, the collection cavity 431 and the cooling groove 310 jointly constitute the air guide channel 410.

[0065] The confluence cavity 460 is configured to collect the cooling air of the cooling groove 310 and the cooling hole 420, and to enable the cooling air to reside in the confluence cavity 460, so as to improve the cooling effect on the discharge portion 30.

[0066] Referring to Figure 3 In the normal installation state, the end of the discharge portion 30 is substantially flush with the inner wall of the flame tube 50, the end of the cooling groove 310 is in communication with the confluence cavity 460, the cooling air from the cooling groove 310 and the cooling hole 420 enters the confluence cavity 460, and resides in the confluence cavity 460, so as to perform convection on the gas inside the flame tube 50 to avoid the gas from being rolled in, and the cooling air in the confluence cavity 460 forms an air film on the discharge portion 30 to protect the discharge portion 30.

[0067] Referring to Figure 4In the ignition transient state, the flame tube 50 expands outwardly more than the combustor casing 60, causing the ignition electrode 70 to extend into the interior of the flame tube 50, at which time the extension of the ignition electrode 70 is increased, the discharge part 30 of the ignition electrode 70 is exposed to the flame, the temperature is increased, at this time, the bottom end of the cooling groove 310 is lowered, causing the gap between the cooling groove 310 and the floating sleeve 430 to be increased, the cooling gas amount is increased, and the cooling of the ignition electrode 70 is strengthened.

[0068] In one embodiment, the end of the discharge part 30 away from the mounting part 20 is closed.

[0069] Referring to Figure 4 When the cooling gas in the converging cavity 460 is transported along the outer end surface of the discharge part 30 to the inside of the flame tube 50, because the discharge part 30 is closed, part of the gas flow is guided along the closure to the central axis region of the discharge part 30, so that the gas film is also formed on the circumferential side of the outer end surface of the discharge part 30, reducing the risk of ablation at the outer end surface of the discharge part 30 due to high temperature.

[0070] To improve the stability of the gas flow on the circumferential side of the discharge part 30, a plurality of cooling grooves 310 are arranged uniformly and circumferentially around the outer circumference of the discharge part 30.

[0071] That is, one cooling groove 310 can be provided on the circumferential side of the discharge part 30, and the cooling groove 310 can be provided around the circumferential side of the discharge part 30.

[0072] The circumferential side of the discharge part 30 can also be provided with a plurality of cooling grooves 310, and the plurality of cooling grooves 310 can be arranged uniformly and circumferentially around the outer circumference of the discharge part 30, which is not limited herein, and the number of cooling grooves 310 can be selected according to the actual flow demand.

[0073] The present application also provides an aero-engine, which comprises a flame tube 50, a casing 60, and the ignition electrode 70 described above, and the ignition electrode 70 is connected to the flame tube 50 and the casing 60, respectively.

[0074] The cooling gas between the casing 60 and the flame tube 50 flows to the circumferential side of the discharge part 30 through the cooling groove 310 and the cooling hole 420, and forms a gas film on the circumferential side of the discharge part 30, thereby reducing the risk of ablation of the discharge part 30 by high-temperature combustion gas.

[0075] In summary, the ignition electrode 70 of the present application is provided with at least one cooling groove 310 on the circumferential side of the discharge part 30 in the axial direction, and the cross-sectional size of the cooling groove 310 decreases in the direction from the mounting part 20 to the flame tube 50, so that when the ignition electrode 70 is in different extension amounts, the flame tube 50 side has different amounts of cooling gas, and the greater the extension amount, the greater the amount of cooling gas, thereby achieving maximum utilization of the cooling gas.

[0076] The end of the discharge part 30 away from the mounting part 20 is closed, so that the cooling gas is dispersed and covered on the end face of the ignition electrode 70, and a separation cavity is formed in the center of the outlet end of the ignition electrode 70, so as to achieve the effect of blocking high-temperature gas and cooling the center of the end of the ignition electrode 70.

[0077] The present application uses specific words to describe the embodiments of the present application. As "one embodiment", "an embodiment", and / or "some embodiments" means a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that the "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned in different positions in the specification does not necessarily mean the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be properly combined.

[0078] 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 solution of the present application, falls within the protection scope defined by the claims of the present application.

Claims

1. An ignition electrode, characterized by, Comprising: a body having an axially arranged mounting portion and a discharge portion, the mounting portion being detachably connected with a casing, the discharge portion being clamped to a flame tube by a floating mounting and extending towards an inner side of the flame tube at one end; at least one cooling groove is formed on an outer circumferential side of the discharge portion along an axial direction thereof, one side port of the cooling groove being in communication with a cavity between the casing and the flame tube, and the other side port of the cooling groove being in communication with an inner cavity of the flame tube; wherein, a cross-sectional dimension of the cooling groove decreases in a direction from the mounting portion to the flame tube; wherein, a passable air volume of the cooling groove increases with an increase of an extension amount of the discharge portion.

2. The ignition tip of claim 1, wherein a gas guide passage is arranged on the floating mounting, and the discharge portion is arranged in the gas guide passage; the cooling groove is in communication with the gas guide passage, and at least one cooling hole is formed on the floating mounting, one side port of the cooling hole being in communication with the cavity between the casing and the flame tube, and the other side port of the cooling hole being in communication with the inner cavity of the flame tube.

3. The igniter tip of claim 2, wherein an angle between a hole diameter of the cooling hole and an axis of the discharge portion is arranged.

4. The igniter tip of claim 2 wherein, the floating mounting comprises a floating sleeve, a cover plate arranged outside the floating sleeve, and a mounting seat connected with the cover plate, one end of the mounting seat being connected with the flame tube; the cooling hole is formed on the floating sleeve, and a plurality of the cooling holes are arranged at intervals around an outer circumferential side of the floating sleeve.

5. The igniter tip of claim 4, wherein an installation hole is formed on the cover plate, one end of the floating sleeve is arranged in the installation hole and clamped in an installation gap between the cover plate and the mounting seat, and the other end of the floating sleeve is designed as a flared portion and has a collection cavity, the collection cavity being in communication with the cooling groove.

6. The igniter tip of claim 5 wherein, a confluence cavity is formed between the mounting seat and the discharge portion and the flame tube, a circumferential cross-sectional dimension of the confluence cavity being greater than a circumferential dimension of the discharge portion; the confluence cavity, the collection cavity, and the cooling groove jointly constitute the gas guide passage.

7. The igniter tip according to any one of claims 1 to 6, characterized in that an end portion of the discharge portion away from the mounting portion is designed as a closed portion.

8. The igniter tip according to any one of claims 1 to 6, characterized in that a plurality of the cooling grooves are arranged at intervals around a circumferential direction of the discharge portion.

9. The igniter tip according to any one of claims 1 to 6, wherein the mounting portion is detachably connected with the casing by threads.

10. An aeroengine characterised in that, Comprising: a flame tube; a casing; the ignition electrode according to any one of claims 1-9 is connected with the flame tube and the casing, respectively.

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