CN114753932A - Oil collecting ring, fuel nozzle, combustion chamber, gas turbine engine and thermal protection method - Google Patents
Oil collecting ring, fuel nozzle, combustion chamber, gas turbine engine and thermal protection method Download PDFInfo
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- CN114753932A CN114753932A CN202110021873.0A CN202110021873A CN114753932A CN 114753932 A CN114753932 A CN 114753932A CN 202110021873 A CN202110021873 A CN 202110021873A CN 114753932 A CN114753932 A CN 114753932A
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 242
- 239000000446 fuel Substances 0.000 title claims abstract description 102
- 238000000034 method Methods 0.000 title claims abstract description 11
- 239000003921 oil Substances 0.000 claims description 373
- 239000000295 fuel oil Substances 0.000 claims description 41
- 238000011144 upstream manufacturing Methods 0.000 claims description 32
- 238000002347 injection Methods 0.000 claims description 19
- 239000007924 injection Substances 0.000 claims description 19
- 238000004939 coking Methods 0.000 description 24
- 239000007789 gas Substances 0.000 description 15
- 239000010410 layer Substances 0.000 description 14
- 230000000694 effects Effects 0.000 description 10
- 238000010438 heat treatment Methods 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 4
- 239000002184 metal Substances 0.000 description 4
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000002035 prolonged effect Effects 0.000 description 3
- 238000000889 atomisation Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000000571 coke Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 238000009736 wetting Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/24—Heat or noise insulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The invention relates to an oil collecting ring, a fuel nozzle, a combustion chamber, a gas turbine engine and a thermal protection method. The oil collecting ring comprises a main combustion stage oil way and a plurality of main combustion stage nozzles, the main combustion stage oil way is an annular main combustion stage oil way, the main combustion stage oil nozzles extend outwards from the main combustion stage oil way, and the main combustion stage oil nozzles are distributed along the circumferential direction of the annular main combustion stage oil way; a pre-combustion main oil way; a precombustion-level auxiliary oil way; the annular main combustion stage oil way and the annular main combustion stage oil way are arranged on the axial side and the radial side of the annular main combustion stage oil way and surround along the annular main combustion stage oil way.
Description
Technical Field
The invention belongs to the technical field of gas turbine engines, and particularly relates to an oil collecting ring, a fuel nozzle, a combustion chamber, a gas turbine engine and a thermal protection method.
Background
The fuel nozzle of the aircraft engine is mainly influenced by the convective heat exchange of air from an outlet of the high-pressure compressor and the radiant heat exchange of fuel gas in the flame tube in the combustion chamber. As the inlet temperature of the combustion chamber increases, the temperature of the fuel line walls within the fuel nozzle and the temperature of the fuel also increase. The high fuel wall wetting temperature enables the fuel to react with dissolved oxygen and deposit and coke on the wall surface of the oil way, thereby reducing the flow area of the fuel pipeline, even blocking a nozzle when the fuel is serious and influencing the atomization effect of the fuel. The increasingly poor fuel atomization results lead to deterioration of combustion efficiency, emissions, and outlet temperature distribution in the combustion chamber, increased fuel consumption of the engine, decreased power performance, and difficulty in ensuring the working life of the turbine blades, which pose a serious threat to flight safety.
Therefore, it is necessary to take thermal protection measures for the nozzle to reduce the heating effect of the external heat source on the fuel oil, so as to avoid the occurrence of coking phenomenon.
According to the results of the previous studies, the following measures are considered to help prevent coking of the fuel injector: (1) fuel oil with better thermal stability is adopted; (2) cooling the nozzle with air or fuel; (3) designing a structure outside the fuel pipeline to reduce heat exchange; (4) the geometric dimension and the thermal protection design of the fuel channel are improved to reduce the wet wall temperature; (5) the surface of the fuel passage is treated to suppress carbon deposition.
Therefore, in the prior art, the main technical scheme for preventing the coking of the fuel nozzle comprises the steps of carrying out effective thermal protection structure design on the nozzle, optimizing a nozzle flow passage structure, improving the surface smoothness to reduce the wet wall temperature and reduce the coking of the fuel nozzle. The thermal protection design of the nozzle mainly adopts the nozzle thermal protection scheme of combining the mutual heat exchange of fuel oil of a main oil path and a secondary oil path and designing an inner thermal insulation cavity and an outer thermal insulation cavity.
In one scheme of the prior art, the precombustion stage oil path and the main combustion stage oil path in the oil collecting ring are respectively arranged in parallel in an annular shape along the axial direction, and the precombustion stage oil path is adjacent to the upstream and the downstream of the main combustion stage oil path in the axial direction. However, the inventor finds that the thermal protection effect of the oil collecting ring of the structure still needs to be improved to ensure that the main combustion stage fuel oil in the oil collecting ring is not coked, the oil collecting ring of the structure has poor universality, the main combustion stage fuel oil nozzle cannot be arranged at the axial downstream end of the main combustion stage, and if the thermal protection effect of the downstream pre-combustion stage oil way is lost after the arrangement, the structure is mainly suitable for a combustion chamber structure with the radial injection direction of the main combustion stage fuel oil nozzle, and the universality is poor.
Accordingly, there is a need in the art for an oil collection ring that addresses the above issues to reduce the risk of coking of the primary stage fuel, extend the life of the fuel nozzles, allow for stable and reliable operation of the combustor and gas turbine engine, and improve the versatility of the oil collection ring and fuel nozzles.
Disclosure of Invention
It is an object of the present invention to provide an oil trap ring.
It is an object of the present invention to provide a fuel injector.
It is an object of the present invention to provide a combustion chamber.
It is an object of the present invention to provide a gas turbine engine.
It is an object of the present invention to provide a method of thermal protection.
An oil gathering ring according to an aspect of the present invention includes: the main combustion stage fuel oil circuit is an annular main combustion stage fuel oil circuit, the main combustion stage fuel oil nozzles extend outwards from the main combustion stage fuel oil circuit, and the main combustion stage fuel oil nozzles are distributed along the circumferential direction of the annular main combustion stage fuel oil circuit; a pre-combustion main oil way; a pre-combustion stage auxiliary oil way; the pre-combustion stage main oil passage and the pre-combustion stage auxiliary oil passage are formed to surround along the annular main combustion stage oil passage at the axial upstream side and the radial inner side of the annular main combustion stage oil passage.
In one or more embodiments of the oil collection ring, the main fuel stage oil path includes at least two main fuel stage oil path branches, the at least two main fuel stage oil path branches constituting an annular main fuel stage oil path; the annular main combustion stage oil way is arranged at the axial upstream side of the annular main combustion stage oil way and surrounds the annular main combustion stage oil way; the auxiliary pre-combustion stage oil way surrounds the annular main combustion stage oil way at the radial inner side of the annular main combustion stage oil way.
In one or more embodiments of the oil collecting ring, the pre-combustion stage main oil passage includes at least two pre-combustion stage main oil passage branches, and the at least two pre-combustion stage main oil passage branches constitute an annular pre-combustion stage main oil passage.
In one or more embodiments of the oil collecting ring, the pre-combustion stage secondary oil passage has only a single oil passage, the single oil passage is a double-layer annular oil passage, a radially inner layer annular oil passage of the double-layer annular oil passage surrounds along the annular main combustion stage oil passage at a radially inner side of the annular main combustion stage oil passage, a radially outer layer annular oil passage of the double-layer annular oil passage surrounds along the annular main combustion stage oil passage at a radially outer side of the annular main combustion stage oil passage, and the radially inner layer annular oil passage and the radially outer layer annular oil passage of the double-layer annular oil passage extend in a radial direction through a U-shaped structure.
In one or more embodiments of the oil collecting ring, the pre-combustion main oil way and the pre-combustion auxiliary oil way are respectively provided with a single oil way, and the profiles of the pre-combustion main oil way, the pre-combustion auxiliary oil way and the main combustion oil way are fitted and matched with each other.
In one or more embodiments of the oil collecting ring, the mutual fit matching structure of the profiles of the main fuel oil path, the auxiliary fuel oil path and the main fuel oil path comprises that the main fuel oil path has a first inclined plane and a first plane, the auxiliary fuel oil path has a second inclined plane and a third inclined plane, and the main fuel oil path has a second plane and a fourth inclined plane, the first inclined plane fits and matches with the second inclined plane, the first plane fits and matches with the second plane, and the third inclined plane fits and matches with the fourth inclined plane.
In one or more embodiments of the oil collecting ring, the injection direction of the fuel nozzles of the main combustion stage can have an axial direction, a radial direction and an oblique direction between the axial direction and the radial direction.
A fuel nozzle according to an aspect of the present invention includes a nozzle housing, a rod core, and an oil collecting ring as described in any one of the above, wherein the oil collecting ring is located in a receiving space provided in the nozzle housing, and the rod core is used for providing fuel for the main stage oil passage, the pre-stage main oil passage, and the pre-stage sub oil passage
In one or more embodiments of the fuel nozzle, a radially side wall or an axially downstream end wall of the nozzle housing has a through bore.
According to one aspect of the invention, the combustion chamber comprises a flame tube, a casing and the fuel nozzle, wherein the fuel output by the oil collecting ring is combusted in the flame tube, and the rod core is fixedly connected to the casing.
A gas turbine engine according to an aspect of the present invention includes a rotor, and the combustion chamber.
According to one aspect of the invention, the thermal protection method is used for an annular main combustion stage oil circuit of an oil collecting ring, and comprises the following steps: and heat exchange is provided for the annular main combustion stage oil path along the annular main combustion stage oil path at the radial side and the axial side of the annular main combustion stage oil path.
In summary, the effects of the present invention include, but are not limited to, one or a combination of the following:
(1) the inventor accurately identifies the key area of coking as the radial inner side and the axial upstream side of the main combustion stage oil way in the process of completing the invention, the axial upstream side and the radial inner side of the annular main combustion stage oil way are surrounded along the annular main combustion stage oil way through the pre-combustion stage main oil way and the pre-combustion stage auxiliary oil way, the main combustion stage oil way is isolated from the convective heat exchange and the heat conduction of the upstream air of the oil collecting ring and the metal wall surface, the coking risk from the upstream of the oil collecting ring on the main combustion stage oil way is effectively reduced, the influence of the inner side of the oil collecting ring of the main combustion stage oil way is isolated, the coking risk on the inner side of the main combustion stage oil way is reduced, the heat protection effect is further improved, the coking risk of the main combustion stage fuel is reduced, the service life of a fuel nozzle is prolonged, the combustion chamber and the gas turbine engine stably and reliably run, and the pre-combustion stage oil way can be arranged only on the radial inner side and the axial upstream side, therefore, the injection direction of the fuel nozzle of the main combustion stage can be radial or axial, the oil collecting ring can be adapted to combustion chambers of more types, and the universality of the oil collecting ring and the fuel nozzle is improved;
(2) A main combustion stage oil way is formed by a plurality of main combustion stage fuel oil branches, so that the circulation length of the main combustion stage oil way fuel oil in the oil collecting ring is shortened, and the fuel oil is sprayed out from the main combustion stage nozzle. The design shortens the heating time of the fuel oil in the main combustion level oil circuit in the oil collecting ring, and reduces the coking risk in the main combustion level oil circuit;
(3) the heat protection area of the pre-combustion stage main oil way to the main combustion stage oil way is increased through the branch of the multi-strand pre-combustion stage main oil way;
(4) through mutual fitting and matching of profiles of the pre-combustion-stage main oil way, the pre-combustion-stage auxiliary oil way and the main combustion-stage oil way, good thermal protection on the main combustion-stage oil way under a compact layout is realized, and the risk of coking of main combustion-stage fuel oil is reduced.
Drawings
The above and other features, characteristics and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and examples, wherein it is to be noted that the drawings are given by way of illustration only, are not drawn to scale, and should not be taken as limiting the scope of the invention, which is actually claimed, wherein:
FIG. 1 is a schematic view of a combustor of a gas turbine engine.
FIG. 2 is a schematic view of a nozzle housing of the fuel nozzle according to the embodiment.
Fig. 3 is a schematic view of an internal structure of a fuel injection nozzle of an embodiment.
Fig. 4 is a schematic diagram of an oil path structure of an oil gathering ring of an embodiment of the fuel nozzle.
Fig. 5A to 5C are schematic structural views of a main combustion stage oil passage, a pre-combustion stage main oil passage, and a main combustion stage auxiliary oil passage of the oil passage shown in fig. 4, respectively.
Fig. 6 is a schematic view of the internal structure of a fuel injection nozzle of another embodiment.
Fig. 7 is a schematic diagram of an oil path structure of an oil gathering ring of another embodiment of the fuel nozzle.
Fig. 8A to 8C are schematic structural views of a main combustion stage oil passage, a pre-combustion stage main oil passage, and a main combustion stage auxiliary oil passage of the oil passage shown in fig. 7, respectively.
Fig. 9 is a schematic structural view of a nozzle housing of a fuel injection nozzle according to still another embodiment.
Fig. 10 is a schematic view of the internal structure of a fuel injection nozzle of still another embodiment.
Detailed Description
The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention.
It should be understood that the terms "first", "second", etc. are used to define the components, and are used only for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, should not be construed as limiting the scope of the present invention. Reference throughout this specification to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic described in connection with at least one embodiment of the present application is included in at least one embodiment of the present application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.
The gas turbine engine takes a turbofan engine as an example and comprises a fan, a gas compressor, a combustion chamber and a turbine, wherein air enters the engine from the fan, enters the combustion chamber after being pressurized by the gas compressor, and is mixed and combusted with fuel oil sprayed by a fuel oil nozzle in the combustion chamber to form high-temperature and high-pressure gas so as to drive the turbine to output power.
Referring to FIG. 1, a combustor of a gas turbine engine includes an oil nozzle 23, a liner 24, and a casing 25. The air flow entering the combustion chamber is divided into three streams, including outer annular cavity air 1, head intake air 2 and inner annular cavity air 3. The fuel nozzle 23 comprises a rod core 4, an oil collecting ring 5 and the like. The rod core 4 is fixedly connected to the casing 25, air is compressed by the compressor and then enters the combustion chamber, the air and fuel oil output by the oil path of the oil collecting ring 5 of the fuel oil nozzle 23 are mixed and then are combusted in the flame tube 24, and the generated high-temperature fuel gas flows backwards to push the turbine to do work.
First embodiment
As shown in fig. 2 to 5C, the fuel nozzle 23 includes a rod core 4, an oil gathering ring 5, and a nozzle housing 31, and the nozzle housing 31 provides a receiving space S to receive the oil gathering ring 5 therein. The specific structure of the nozzle housing 31 may include a radially inner wall 311 and a radially outer wall 312, and a radial gap between the radially inner wall 311 and the radially outer wall 312 defines the receiving space S.
The oil collecting ring 5 has an oil collecting ring body 34, and an oil passage located inside the oil collecting ring body 34, such as shown in fig. 3 to 5C, including a main combustion stage oil passage 35, a pre-combustion stage main oil passage 36, and a pre-combustion stage auxiliary oil passage 37. The rod core 4 is used for providing fuel for the main combustion stage oil path 35, the pre-combustion stage main oil path 37 and the pre-combustion stage auxiliary oil path 36. The primary combustion stage oil passage 35 is annular, the plurality of primary combustion stage nozzle orifices 33 extend outwardly from the primary combustion stage oil passage 35, and the plurality of primary combustion stage fuel nozzle orifices 33 are distributed circumferentially of the annular primary combustion stage oil passage 35 about the collector ring central axis 42. As shown in fig. 3, 4 and 5A, a plurality of primary stage nozzle orifices 33 extend in an axially downstream direction, and the axially downstream end wall of the nozzle housing 31 is provided with through holes 32 for the primary stage fuel passage orifices 33 to project and inject fuel, but not limited thereto.
With continued reference to fig. 3 to 5C, the pre-combustion stage main oil passage 36 and the pre-combustion stage sub-oil passage 37 are formed on the axial upstream side and the radial inside of the annular main combustion stage oil passage 35 and surround the annular main combustion stage oil passage 35, so that the beneficial effects and principles of the structure are that the inventor accurately identifies that the key areas where coking occurs are the radial inside and the axial upstream side of the main combustion stage oil passage in the process of completing the present invention, and through the formation of the pre-combustion stage main oil passage and the pre-combustion stage sub-oil passage on the axial upstream side and the radial inside of the annular main combustion stage oil passage and surround the annular main combustion stage oil passage, the main combustion stage oil passage is isolated from the convection heat exchange and the heat conduction of the upstream air of the oil collecting ring and the metal wall surface, the coking risk of the main combustion stage oil passage from the upstream of the oil collecting ring is effectively reduced, and the influence of the inside of the oil collecting ring of the main combustion stage oil passage is isolated, and the coking risk of the inside of the main combustion stage oil passage is reduced, therefore, the heat protection effect is further improved, the risk of coking of the main combustion stage fuel is reduced, the service life of the fuel nozzle is prolonged, the combustion chamber and the gas turbine engine can stably and reliably run, and the pre-combustion stage oil way can be arranged only on the radial inner side and the axial upstream side, so that the injection direction of the main combustion stage fuel nozzle can be radial, axial and oblique between the radial inner side and the axial upstream side, the oil collecting ring can be adapted to combustion chambers of more models, and the universality of the oil collecting ring and the fuel nozzle is improved.
With continued reference to fig. 4 and 5A, the main fuel stage oil path 35 includes two main fuel stage oil path branches 351 and 352, but not limited thereto, it is understood that a greater number of branches may be provided, and the two main fuel stage oil path branches 351 and 352 form the annular main fuel stage oil path 35; the precombustion stage main oil passage 37 is surrounded along the annular main combustion stage oil passage 35 on the axially upstream side of the annular main combustion stage oil passage 35; the precombustion stage secondary oil passage 36 is surrounded along the annular main combustion stage oil passage 35 radially inside the annular main combustion stage oil passage 35. The beneficial effect that so realize lies in, constitutes main burning level oil way 35 through stranded main burning level fuel branch road for the circulation length of fuel in the main burning level oil way 35 in the oil gathering ring shortens, and the fuel spouts from main burning level spout 33 through shorter circulation length, and this design has shortened the heating time of the fuel in the oil gathering ring of main burning level oil way 35, has reduced the coking risk in the main burning level oil way. Similarly, referring to fig. 4 and 5C, the pre-combustion main oil path 37 may include two pre-combustion main oil path branches 371 and 372, but not limited thereto, it is understood that a plurality of branches may be provided, the two pre-combustion main oil path branches 371 and 372 form the annular pre-combustion main oil path 37, the two branches are divided into two parts after entering the oil collecting ring body 34, the fuel oil circles around the main combustion main oil path 35 in the pre-combustion main oil path 37, and the fuel oil is combined into one in the two pre-combustion main oil path branches 371 and 372 and led out from the oil collecting ring 34. The design that the precombustion stage main oil path 37 is divided into a plurality of parts increases the protection area of the precombustion stage main oil path 37 to the main combustion stage oil path 35, isolates the convective heat transfer and the heat conduction of the upstream air of the oil collecting ring body 34 and the metal wall surface of the main combustion stage oil path 35, and effectively reduces the coking risk of the upstream air from the oil collecting ring body 34 on the main combustion stage oil path 35.
With continued reference to fig. 4 and 5B, the pre-combustion stage secondary oil passage 36 has only a single oil passage, which is a double-layer annular oil passage, and the radially inner annular oil passage 361 of the double-layer annular oil passage surrounds the annular main combustion stage oil passage 35 at the radially inner side of the annular main combustion stage oil passage 35, and it can be understood that, when the injection direction of the main combustion stage fuel nozzle 33 is axial, the radially outer side of the main combustion stage oil passage 35 may also surround the radially inner side of the main combustion stage oil passage 35 on the basis of surrounding the main combustion stage oil passage 35, that is, the radially outer annular oil passage 362 of the double-layer annular oil passage surrounds the annular main combustion stage oil passage 35 at the radially outer side of the annular main combustion stage oil passage 35, and as shown in fig. 5B, the radially inner annular oil passage 361 of the double-layer annular oil passage and the radially outer annular oil passage 362 are connected by a U-shaped structure 363 extending in the radial direction. The flow path of the fuel in the auxiliary oil path 36 of the pre-combustion stage may be that after entering the oil collecting ring body 34, the fuel circles around the inner side of the main combustion stage oil path 35, that is, after circles around the radially inner annular oil path 361, turns around through the U-shaped structure 363, circles around the outer side of the main combustion stage oil path 35, that is, turns around through the U-shaped structure 363, circles around the radially outer annular oil path 362, and finally is led out from the oil collecting ring 34. The auxiliary oil way 36 has the beneficial effects that the arrangement scheme of the auxiliary oil way 36 isolates the influence of the inner side and/or the outer side (if the injection direction is the axial direction, an outer layer oil way can be arranged) of the main combustion stage oil way 35 on the oil gathering ring 34, and the coking risk of the inner side of the main combustion stage oil way 35 is reduced. The oil collecting ring 34 may be machined by, for example, additive manufacturing, so as to form the oil passages integrally.
Second embodiment
The parts of the second embodiment that are identical to the parts of the first embodiment will not be described in detail here.
Referring to fig. 6 to 8C, the oil gathering ring of the second embodiment is more compact in structure than the first embodiment. As shown in fig. 8A, the main fuel stage oil passage 35 also includes two main fuel stage oil passage branches 351 and 352, as in the first embodiment. As shown in fig. 8B, the precombustion stage secondary oil path 36 is a single oil path and is in a single-layer ring shape, instead of the double-layer ring shape of the first embodiment, as shown in fig. 6 and 7, the precombustion stage secondary oil path 36 of the second embodiment is one in the oil collecting ring 34, is located radially inside the main combustion stage oil path 35 in the oil collecting ring 34, and is led out from the oil collecting ring 34 by being wound around the main combustion stage oil path 35. As shown in fig. 8C, the pilot stage main oil path 37 is a single oil path, and instead of the first embodiment having two pilot stage main oil path branches 371 and 372, as shown in fig. 6 and 7, the pilot stage main oil path 37 of the second embodiment is a single oil path in the oil collecting ring 34, and the single oil path is located axially upstream of the main stage oil path 35 in the oil collecting ring 34, and led out from the oil collecting ring 34 after being wound around the main stage oil path 35. Referring to fig. 6, the profiles of the pre-combustion stage main oil path 37, the pre-combustion stage auxiliary oil path 36 and the main combustion stage oil path 35 are fitted and matched with each other, so that the compact arrangement of the oil paths can be realized, the spacing between the three oil paths is reduced, the heat exchange area between the three oil paths and the heat conduction quantity between the three oil paths are increased, the pre-combustion stage auxiliary oil path 36 and the pre-combustion stage main oil path 37 not only isolate the heating of the main combustion stage oil path 35 from the outside of the oil collecting ring, but also increase the active cooling effect of the main combustion stage oil path 35, and the heat protection effect similar to that of the first embodiment is obtained.
Referring to fig. 6, the specific structure of the mutual matching of the profiles may be that the main combustion stage oil path 35 has a first inclined plane 3501 and a first plane 3502, the precombustion stage secondary oil path 36 has a second plane 3602 and a third inclined plane 3603, and the precombustion stage main oil path 37 has a second inclined plane 3702 and a fourth inclined plane 3704, the first inclined plane 3501 matches the second inclined plane 3702, the first plane 3502 matches the second plane 3602, and the third inclined plane 3603 matches the fourth inclined plane 3704. It will be understood by those skilled in the art that the specific structure of the fit-fit is not limited to that shown in the drawings, and other structures are possible, such as a cambered surface fit-fit, a slant surface fit-fit in the drawings, and a plane fit-fit structure, which are easy to machine.
Third embodiment
The parts of the third embodiment that are identical to the parts of the first embodiment will not be described in detail here.
Referring to fig. 9 and 10, the injection direction of the fuel nozzle 33 of the third embodiment is a radial direction, but not the injection direction of the first and second embodiments is an axial direction. An oil collecting ring 34 is positioned inside the nozzle shell 31, and a main combustion stage oil path 35, a pre-combustion stage auxiliary oil path 36 and a pre-combustion stage main oil path 37 are positioned inside the oil collecting ring 34. The main combustion stage oil path 35 is located in the middle of the oil collecting ring 34, the auxiliary pre-combustion stage oil path 36 is located inside and downstream of the main combustion stage oil path 35, and the main pre-combustion stage oil path 37 is located upstream of the main combustion stage oil path 35. The radially outer wall 312 of the nozzle housing 31 is perforated with the through holes 32 for the extension of the primary stage fuel nozzle orifices 33 and the injection of fuel, the primary stage nozzle orifices 33 also being circumferentially disposed along the oil catcher ring central axis 42.
Because the pre-combustion stage oil way can be arranged only on the radial inner side and the axial upstream side, the injection direction of the main combustion stage fuel nozzle can be radial, axial or oblique between the radial and the axial, the oil collecting ring can be adapted to combustion chambers of more types, and the universality of the oil collecting ring and the fuel nozzle is improved.
It is understood that, after the injection direction of the fuel nozzle 33 is confirmed in the design stage, a pilot stage oil path may be further increased on the radially inner side and the axially upstream side, for example, if the injection direction of the fuel nozzle 33 is confirmed to be axially downstream as in the first embodiment, a pilot stage oil path may be further increased on the radially outer side, and if the injection direction of the fuel nozzle 33 is confirmed to be radially outward as in the third embodiment, a pilot stage oil path may be further increased on the axially downstream side, and of course, as in the second embodiment, a compact structure may be provided with only pilot stage oil paths arranged on the radially inner side and the axially upstream side.
As described above, according to the above embodiments, the method for protecting the annular main fuel stage oil passage of the oil collecting ring from heat may include surrounding the annular main fuel stage oil passage 35 on both the radially inner side and the axially upstream side of the annular main fuel stage oil passage 35, and providing heat exchange to the annular main fuel stage oil passage 35, for example, as shown in the first, second, and third embodiments, the precombustion stage sub oil passage 36 surrounds the annular main fuel stage oil passage 35 on the radially inner side, and the precombustion stage main oil passage 37 surrounds the annular main fuel stage oil passage 35 on the axially upstream side.
To sum up, the oil collecting ring, the fuel nozzle and the thermal protection method adopting the embodiment at least have the beneficial effects that:
(1) the inventor accurately identifies the key areas of coking as the radial inner side and the axial upstream side of the main combustion stage oil way, the axial upstream side and the radial inner side of the annular main combustion stage oil way are surrounded along the annular main combustion stage oil way through the pre-combustion stage main oil way and the pre-combustion stage auxiliary oil way, the main combustion stage oil way is isolated from the convective heat exchange and the heat conduction of the upstream air of the oil collecting ring and the metal wall surface, the coking risk of the upstream of the oil collecting ring on the main combustion stage oil way is effectively reduced, the influence of the inner side of the oil collecting ring of the main combustion stage oil way is isolated, the coking risk of the inner side of the main combustion stage oil way is reduced, the thermal protection effect is further improved, the coking risk of the main combustion stage fuel oil is reduced, the service life of a fuel nozzle is prolonged, a combustion chamber and a gas turbine engine stably and reliably run, and because the pre-combustion stage oil way can be arranged only on the radial inner side and the axial upstream side, therefore, the injection direction of the main combustion stage fuel nozzle can be radial or axial, the oil collecting ring can be adapted to more types of combustion chambers, and the universality of the oil collecting ring and the fuel nozzle is improved;
(2) A main combustion stage oil way is formed by a plurality of main combustion stage fuel oil branches, so that the circulation length of the main combustion stage oil way fuel oil in the oil collecting ring is shortened, and the fuel oil is sprayed out from the main combustion stage nozzle. The design shortens the heating time of the fuel oil of the main fuel level oil circuit in the oil collecting ring, and reduces the coking risk in the main fuel level oil circuit;
(3) the heat protection area of the pre-combustion main oil way to the main combustion oil way is increased through the multi-strand pre-combustion main oil way branch;
(4) the profiles of the pre-combustion-stage main oil way, the pre-combustion-stage auxiliary oil way and the main combustion-stage oil way are mutually attached and matched, so that good thermal protection on the main combustion-stage oil way under a compact layout is realized, and the risk of coking of the main combustion-stage fuel oil is reduced.
Although the present invention has been disclosed in the above-mentioned embodiments, it is not intended to limit the present invention, and those skilled in the art may make variations and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (12)
1. An oil gathering ring, comprising:
The main combustion stage fuel oil circuit is an annular main combustion stage fuel oil circuit, the main combustion stage fuel oil nozzles extend outwards from the main combustion stage fuel oil circuit, and the main combustion stage fuel oil nozzles are distributed along the circumferential direction of the annular main combustion stage fuel oil circuit;
a pre-combustion main oil way;
a pre-combustion stage auxiliary oil way;
the pre-combustion stage main oil passage and the pre-combustion stage auxiliary oil passage are formed to surround along the annular main combustion stage oil passage at the axial upstream side and the radial inner side of the annular main combustion stage oil passage.
2. The oil gathering ring as recited in claim 1 wherein the primary fuel stage oil passage includes at least two primary fuel stage oil passage branches forming an annular primary fuel stage oil passage; the pre-combustion stage main oil way surrounds along the annular main combustion stage oil way on the axial upstream side of the annular main combustion stage oil way; the auxiliary oil passage of the pre-combustion stage is surrounded along the annular main combustion stage oil passage at the radial inner side of the annular main combustion stage oil passage.
3. The oil collecting ring according to claim 1, wherein the pilot stage main oil passage includes at least two pilot stage main oil passage branches constituting an annular pilot stage main oil passage.
4. The oil collecting ring according to claim 1, wherein the auxiliary oil passage of the pre-combustion stage has only a single oil passage, the single oil passage is a double-layer annular oil passage, a radially inner layer annular oil passage of the double-layer annular oil passage is surrounded along the annular main combustion stage oil passage at a radially inner side of the annular main combustion stage oil passage, a radially outer layer annular oil passage of the double-layer annular oil passage is surrounded along the annular main combustion stage oil passage at a radially outer side of the annular main combustion stage oil passage, and the radially inner layer annular oil passage and the radially outer layer annular oil passage of the double-layer annular oil passage extend in a radial direction through a U-shaped structure.
5. The oil collecting ring as claimed in claim 1, wherein the pre-combustion stage main oil passage and the pre-combustion stage secondary oil passage each have only a single oil passage, and the profiles of the pre-combustion stage main oil passage, the pre-combustion stage secondary oil passage and the main combustion stage oil passage are fitted and matched with each other.
6. The oil collecting ring of claim 5, wherein the profile matching structure of the pre-combustion stage main oil passage, the pre-combustion stage secondary oil passage and the main combustion stage oil passage comprises that the main combustion stage oil passage has a first inclined surface and a first plane, the pre-combustion stage secondary oil passage has a second plane and a third inclined surface, and the pre-combustion stage main oil passage has a second inclined surface and a fourth inclined surface, the first inclined surface is matched with the second inclined surface in a fitting manner, the first plane is matched with the second plane in a fitting manner, and the third inclined surface is matched with the fourth inclined surface in a fitting manner.
7. The oil collecting ring as claimed in any one of claims 1 to 6, wherein the injection direction of the fuel nozzles of the main combustion stage has an axial direction, a radial direction and an oblique direction between the axial direction and the radial direction.
8. A fuel nozzle comprising a nozzle housing, a rod core, and the oil collecting ring of any one of claims 1 to 7, wherein the oil collecting ring is located in a receiving space provided in the nozzle housing, and the rod core is used for providing fuel for the main stage fuel passage, the pre-stage main fuel passage, and the pre-stage secondary fuel passage.
9. The fuel injector of claim 8, wherein the radially outer wall or the axially downstream end wall of the injector housing has the passage aperture.
10. A combustion chamber comprising a flame tube, a casing, and a fuel nozzle as claimed in claim 8 or 9, wherein said oil path of said oil gathering ring outputs fuel to be combusted in said flame tube, and said rod core is fixedly attached to said casing.
11. A gas turbine engine comprising a rotor and a combustor as claimed in claim 10.
12. A thermal protection method is used for an annular main combustion stage oil way of an oil collecting ring, and is characterized by comprising the following steps: and heat exchange is provided for the annular main combustion stage oil path along the annular main combustion stage oil path at the radial side and the axial side of the annular main combustion stage oil path.
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| CN202110021873.0A CN114753932A (en) | 2021-01-08 | 2021-01-08 | Oil collecting ring, fuel nozzle, combustion chamber, gas turbine engine and thermal protection method |
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| CN202110021873.0A CN114753932A (en) | 2021-01-08 | 2021-01-08 | Oil collecting ring, fuel nozzle, combustion chamber, gas turbine engine and thermal protection method |
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| CN202110021873.0A Pending CN114753932A (en) | 2021-01-08 | 2021-01-08 | Oil collecting ring, fuel nozzle, combustion chamber, gas turbine engine and thermal protection method |
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