CN112050253A - Multiple thermal-insulated fuel nozzle - Google Patents
Multiple thermal-insulated fuel nozzle Download PDFInfo
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- CN112050253A CN112050253A CN202010988344.3A CN202010988344A CN112050253A CN 112050253 A CN112050253 A CN 112050253A CN 202010988344 A CN202010988344 A CN 202010988344A CN 112050253 A CN112050253 A CN 112050253A
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The patent relates to the field of aircraft engines, in particular to a multiple heat insulation fuel nozzle, which comprises a nozzle body and an oil circuit system, wherein the oil circuit system is arranged in the nozzle body and comprises at least one group of oil circuits; the oil path comprises an inlet, a middle section and a nozzle front flow passage; at least two middle section heat insulation layers are arranged on the periphery of the middle section; the middle section heat insulation layer is arranged in the nozzle body; the nozzle front flow channel is of a segmented structure and comprises an end section and at least one front section, the end section is an annular flow channel, and the at least one front section is a C-shaped flow channel. The fuel nozzle provided by the invention has the advantages that the fuel flow channel is optimally designed aiming at the conditions of high fuel coking risk and high flow resistance loss at high temperature, and meanwhile, the thermal protection measures of the nozzle are increased.
Description
Technical Field
The patent relates to the field of aircraft engines, and mainly relates to a multiple heat-insulation fuel nozzle.
Background
Fuel nozzles are key components of aircraft engines and play an important role in engine performance. The fuel nozzle has the functions of atomizing (or vaporizing) fuel, accelerating the formation of mixed gas, ensuring stable combustion and improving combustion efficiency.
With the continuous development of advanced aviation technology, the requirements of cooling devices such as an electronic device, a cockpit, hydraulic pressure and lubricating oil of an airplane by using fuel oil as a coolant are rapidly increased, and the thermal load of the fuel oil is continuously increased, so that the temperature of the fuel oil is increased to 100-140 ℃ before the fuel oil enters a fuel oil nozzle; meanwhile, with the continuous improvement of the pressure ratio of the engine, the inlet temperature of the combustion chamber is further improved to over 900K, and the heating effect on the fuel nozzle of the main combustion chamber cannot be ignored. When the oil temperature in the fuel nozzle exceeds 400K, the oil coking and carbon deposition rate in the nozzle is greatly increased along with the continuous increase of the oil temperature, the service life of the nozzle is greatly reduced, and the aerodynamic performance of an engine is poor. Therefore, a fuel nozzle with a thermal protection structure is needed to be designed so as to effectively prevent the generation of fuel coking and carbon deposition in the fuel nozzle.
Disclosure of Invention
The invention aims to provide a structural scheme of a fuel nozzle, which is provided with multiple heat insulation protective layers, so that the temperature rise of fuel in the fuel nozzle can be reduced, the service life of the fuel nozzle is prolonged, and the performance of an engine is improved.
In order to achieve the purpose, the invention provides the following technical scheme:
the invention provides a multiple heat insulation fuel nozzle which comprises a nozzle body and an oil circuit system, wherein the oil circuit system is arranged in the nozzle body and comprises at least one group of oil circuits; the oil way comprises an inlet, a middle section and a nozzle front flow passage; the maximum length of the flow cross section of the inlet in the axial direction of the engine is smaller than the maximum length of the flow cross section of the inlet in the direction perpendicular to the axial direction of the engine; the maximum length of the flow cross section of the middle section in the axial direction of the engine is smaller than the maximum length of the flow cross section of the middle section perpendicular to the axial direction of the engine;
at least two middle section heat insulation layers are arranged on the periphery of the middle section; the middle section heat insulation layer is arranged in the nozzle body;
the nozzle front flow passage is of a segmented structure and comprises an end section and at least one front section, the end section is an annular flow passage, and the at least one front section is a C-shaped flow passage.
Furthermore, the oil way also comprises a switching section; the switching section is arranged between the inlet and the middle section, and the flow section is gradually reduced along the fuel flow direction; the maximum length of each flow cross section of the adapter section in the axial direction of the engine is smaller than the maximum length of each flow cross section in the direction perpendicular to the axial direction of the engine.
Furthermore, at least one layer of head heat insulation layer is arranged on the periphery of the nozzle front flow passage and is arranged in the nozzle body.
Further, the oil path system comprises a main oil path and an auxiliary oil path; the main oil way is used for supplying oil to a main nozzle; the auxiliary oil way is used for supplying oil to the auxiliary nozzle; the fuel nozzle further comprises a middle oil way, one end of the middle oil way is connected with the tail end of the middle section of the main oil way, and the middle oil way is used for supplying oil through the middle nozzle when the fuel requirement of the auxiliary nozzle is high.
Further, the tail section of the middle oil way is arranged in a head heat insulation layer of the auxiliary oil way.
Further, the nozzle body is made by an additive manufacturing method.
Further, the middle section heat insulation layer and the head heat insulation layer are vacuum heat insulation layers.
Further, the middle section heat insulation layer and the head heat insulation layer are air heat insulation layers.
Furthermore, the thickness of the middle section heat-insulating layer and the head heat-insulating layer is 0.5-1.5 mm.
By adopting the technical scheme, the invention can bring the following beneficial effects:
the fuel nozzle provided by the invention has the advantages that aiming at the conditions of high fuel coking risk and high flow resistance loss at high temperature, the fuel flow channel is optimally designed, and meanwhile, the thermal protection measures of the nozzle are increased:
1. a flow passage switching section is additionally arranged between the fuel inlet and the fuel flow passage, so that the flow resistance loss caused by sudden change of the section of the flow passage is reduced.
2. The section of the fuel oil flow channel adopts a non-circular design, and a heat insulation layer in the shell is designed to be surrounded by a whole ring, so that the installation space of the rod part of the nozzle is saved; independent heat insulation layers are designed on the periphery of the flow channel in the shell and between the flow channel, and a heat insulation sleeve outside the shell provides multiple heat insulation protective layers for fuel oil at the rod part of the nozzle, so that the thickness of the nozzle body in the axial direction of an engine is not increased, and the risk of coking and deposition of the fuel oil at the rod part of the nozzle is reduced.
3. The fuel flow channels of the main nozzle are designed in a segmented mode, the section of one segment of the fuel flow channel is designed to be a circular ring with a sector with a certain angle, the flow area of fuel is reduced, the flow speed of the fuel is increased, and the fuel coking and depositing speed is favorably reduced. Thermal insulation layers are designed outside the main nozzle and the middle nozzle flow passage, so that the risk of coking and deposition of fuel at the head part of the nozzle is reduced.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings needed to be used in the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present disclosure, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
In order to more clearly illustrate the technical solution of the present invention, some brief descriptions will be given below to the drawings used in the description of the embodiment or the prior art.
Fig. 1 is a schematic structural view of one embodiment of a fuel injection nozzle according to the present invention.
FIG. 2 is a schematic cross-sectional view of the fuel injector of FIG. 1 taken along line A-A;
FIG. 3 is an enlarged schematic view of the inlet structure of the fuel injector of FIG. 1;
FIG. 4 is an enlarged schematic view of the fuel nozzle tip configuration of FIG. 1;
FIG. 5 is a schematic cross-sectional view of the fuel injector of FIG. 4 in the direction B-B;
FIG. 6 is a schematic cross-sectional view of the fuel injector of FIG. 4 in the direction C-C;
wherein:
1-main nozzle, 2-head heat insulation ring of main nozzle, 3-head heat insulation ring of auxiliary nozzle, 4-middle nozzle, 5-auxiliary nozzle, 6-swirl core, 7-plug, 8-heat insulation sleeve, 9-nozzle main body, 10-nozzle inlet, 11-nozzle head, 20-main oil inlet, 21-main oil middle section, 22-main oil transfer section, 23-nozzle front flow channel of main oil way, 24-nozzle front flow channel front section of main oil way, 25-nozzle front flow channel end section of main oil way, 30-first heat insulation layer, 31-second heat insulation layer, 32-third heat insulation layer, 33-fourth heat insulation layer, 34-fifth heat insulation layer, 40-auxiliary oil inlet, 41-auxiliary oil middle section, 42-auxiliary oil transfer section, 43-nozzle front flow passage of auxiliary oil passage, 50-middle oil passage.
Detailed Description
The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.
The embodiments of the present disclosure are described below with specific examples, and other advantages and effects of the present disclosure will be readily apparent to those skilled in the art from the disclosure in the specification. It is to be understood that the described embodiments are merely illustrative of some, and not restrictive, of the embodiments of the disclosure. The disclosure may be embodied or carried out in various other specific embodiments, and various modifications and changes may be made in the details within the description without departing from the spirit of the disclosure. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present disclosure, and the drawings only show the components related to the present disclosure rather than the number, shape and size of the components in actual implementation, and the type, amount and ratio of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details. In one embodiment of the present invention, a multiple thermal insulation fuel nozzle is provided, as shown in fig. 1, including a nozzle body and an oil path system, the oil path system is disposed in the nozzle body and includes at least one set of oil paths; the oil path comprises an inlet, a middle section and a nozzle front flow passage; the maximum length of the flow cross section of the inlet in the axial direction of the engine is smaller than the maximum length of the flow cross section of the inlet in the direction perpendicular to the axial direction of the engine; the maximum length of the flow cross section of the middle section in the axial direction of the engine is smaller than the maximum length of the flow cross section of the middle section perpendicular to the axial direction of the engine;
at least two middle section heat insulation layers are arranged on the periphery of the middle section; the middle section heat insulation layer is arranged in the nozzle body;
the nozzle front flow channel is of a segmented structure and comprises an end section and at least one front section, the end section is an annular flow channel, and the at least one front section is a C-shaped flow channel.
In this embodiment, the oil path further includes an adapter section; the switching section is arranged between the inlet and the middle section, and the flow section is gradually reduced along the flow direction of the fuel oil; the maximum length of each flow cross section of the adapter section in the axial direction of the engine is smaller than the maximum length of each flow cross section in the direction perpendicular to the axial direction of the engine.
In this embodiment, the periphery of the nozzle front runner is provided with at least one layer of head heat insulation layer, and the head heat insulation layer is arranged in the nozzle body.
In the present embodiment, the oil passage system includes a primary oil passage and a secondary oil passage; the main oil path is used for supplying oil to the main nozzle 1; the auxiliary oil way is used for supplying oil to the auxiliary nozzle 2; the fuel nozzle further comprises an intermediate oil path 50, one end of the intermediate oil path 50 is connected with the tail end of the middle section of the main oil path and is used for supplying oil through the intermediate nozzle when the fuel requirement of the auxiliary nozzle 2 is high.
In the present embodiment, the end section of the intermediate oil passage 50 is provided in the head heat insulating layer of the sub oil passage.
In this embodiment, the nozzle body is made by an additive manufacturing method.
In this embodiment, the mid-section insulation layer and the head insulation layer are vacuum insulation layers.
In this embodiment, the intermediate section insulation and the head insulation are air insulation.
In this embodiment, the thickness of interlude insulating layer and head insulating layer is 0.5 ~ 1.5 mm.
In the present embodiment, as shown in fig. 1, the relative relationship of the main nozzle 1, the head heat insulating ring 2 of the main nozzle, the head heat insulating ring 3 of the sub-nozzle, the middle nozzle 4, the sub-nozzle 5, the swirl core 6, the plug 7, the heat insulating jacket 8, and the nozzle main body 9 is described.
As shown in fig. 2, the fuel nozzle stem portion includes: 23-nozzle front flow channel of main oil path, 30-first heat insulation layer, 31-second heat insulation layer, 32-third heat insulation layer and 43-nozzle front flow channel of auxiliary oil path.
In this embodiment, the nozzle body 9 has a nozzle front flow passage 23 of the main oil passage and a nozzle front flow passage 43 of the auxiliary oil passage at the stem portion thereof, the second heat insulating layer 31 surrounds the nozzle front flow passage 23 of the main oil passage and the nozzle front flow passage 43 of the auxiliary oil passage, and the nozzle front flow passage 23 of the main oil passage and the nozzle front flow passage 43 of the auxiliary oil passage are separated by the third heat insulating layer 32. The nozzle body 9 surrounds the first thermally insulating layer 30. The cross sections of the nozzle front flow passage 23 of the main oil passage and the nozzle front flow passage 43 of the auxiliary oil passage are in an oval shape; the second heat insulation layer 31 is of a whole ring structure; the third heat insulation layer 32 is positioned in the middle of the flow channels and mainly blocks heat radiation between the flow channels; the first heat insulation layer 30 is a semi-ring structure, which mainly blocks heat radiation of high-temperature gas on the windward side of the nozzle, and in another alternative, the first heat insulation layer 30 may also be a whole ring structure.
FIG. 3 is an enlarged view of an inlet structure of an embodiment of a fuel injector according to the present invention; as shown in the figure: the main features of the fuel nozzle inlet include: 20-main oil inlet, 21-main oil middle section, 22-main oil switching section, 23-nozzle front flow channel of main oil circuit, 40-auxiliary oil inlet, 41-auxiliary oil middle section, 42-auxiliary oil switching section and 43-nozzle front flow channel of auxiliary oil circuit.
In this embodiment, the fuel in the fuel manifold enters the nozzle from the main oil inlet 20 and the auxiliary oil inlet 40, flows through the main oil intermediate section 21 and the auxiliary oil intermediate section 41 midway, and enters the nozzle front flow passage 23 of the main oil passage and the nozzle front flow passage 43 of the auxiliary oil passage after being accelerated by the main oil transition section 22 and the auxiliary oil transition section 42. The cross section shapes of the flow channels of the main oil middle section 21 and the auxiliary oil middle section 41 are oblong, the main oil switching section 22 and the auxiliary oil switching section 42 are convergent, the cross section shapes of the flow channels are oblong, the maximum cross section size of the flow channels is consistent with the cross section size of the flow channel of the middle section, the minimum cross section size of the flow channel is consistent with the cross section size of the flow channel of the rod part, and the cross section sizes of the middle parts are gradually reduced according to a certain angle. The convergent switching section flow channel can effectively reduce the flow resistance loss of fuel oil.
Referring to fig. 4, which is an enlarged view of a head structure of an embodiment of a fuel injection nozzle according to the present invention, fig. 5 is a schematic sectional view of a head portion in a direction B-B, and fig. 6 is a schematic sectional view of a head portion in a direction C-C; as shown in the figure: the main features of the fuel nozzle head include: 23-a nozzle front flow passage of the main oil way, 24-a nozzle front flow passage front section of the main oil way, 25-a nozzle front flow passage tail section of the main oil way, 33-a fourth heat insulation layer, 34-a fifth heat insulation layer and 50-a middle oil way.
In this embodiment, the intermediate oil passage 50 is led out from the nozzle front flow passage 23 of the main oil passage and communicated with the intermediate nozzle 4 through the main and auxiliary connecting sections. The fuel oil flows through the middle oil path 50 and enters the middle nozzle 4, so that the fuel oil can be supplemented to the pre-burning stage of the fuel nozzle in a large state, and the performance of the engine is improved. The fuel flow passage of the main nozzle is divided into a nozzle front flow passage front section 24 of the main oil passage and a nozzle front flow passage tail section 25 of the main oil passage, and the inner diameter and the outer diameter of the two flow passages are kept consistent. The section of the front section 24 of the nozzle front flow passage of the main oil passage is a circular ring with a certain angle sector, the section of the rear section 25 of the nozzle front flow passage of the main oil passage is a complete circular ring, the flow speed of fuel oil in the flow passage 1 is high, and the risk of coking deposition can be reduced. The fourth heat insulation layer 33 surrounds the middle nozzle 4 to provide heat insulation protection for fuel oil in the middle nozzle and the auxiliary nozzle flow passage, and the fifth heat insulation layer 34 surrounds the main nozzle 1 to provide heat insulation protection for fuel oil in the main nozzle flow passage.
The above description is only for the specific embodiments of the present disclosure, but the scope of the present disclosure is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present disclosure should be covered within the scope of the present disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.
Claims (9)
1. A multiple heat insulation fuel nozzle comprises a nozzle body and an oil path system, wherein the oil path system is arranged in the nozzle body and comprises at least one group of oil paths; the oil way comprises an inlet, a middle section and a nozzle front flow passage; the method is characterized in that: the maximum length of the flow cross section of the inlet in the axial direction of the engine is smaller than the maximum length of the flow cross section of the inlet in the direction perpendicular to the axial direction of the engine; the maximum length of the flow cross section of the middle section in the axial direction of the engine is smaller than the maximum length of the flow cross section of the middle section perpendicular to the axial direction of the engine;
at least two middle section heat insulation layers are arranged on the periphery of the middle section; the middle section heat insulation layer is arranged in the nozzle body;
the nozzle front flow passage is of a segmented structure and comprises an end section and at least one front section, the end section is an annular flow passage, and the at least one front section is a C-shaped flow passage.
2. The fuel injector of claim 1, wherein: the oil circuit also comprises a switching section; the switching section is arranged between the inlet and the middle section, and the flow section is gradually reduced along the fuel flow direction; the maximum length of each flow cross section of the adapter section in the axial direction of the engine is smaller than the maximum length of each flow cross section in the direction perpendicular to the axial direction of the engine.
3. The fuel injector of claim 1, wherein: the periphery of the nozzle front runner is provided with at least one layer of head heat insulation layer, and the head heat insulation layer is arranged in the nozzle body.
4. The fuel injector of claim 1, wherein: the oil way system comprises a main oil way and an auxiliary oil way; the main oil way is used for supplying oil to a main nozzle; the auxiliary oil way is used for supplying oil to the auxiliary nozzle; the fuel nozzle further comprises a middle oil way, one end of the middle oil way is connected with the tail end of the middle section of the main oil way, and the middle oil way is used for supplying oil through the middle nozzle when the fuel requirement of the auxiliary nozzle is high.
5. The fuel injector of claim 4, wherein: and the tail section of the middle oil way is arranged in the heat insulation layer of the head part of the auxiliary oil way.
6. The fuel injector of claim 1, wherein: the nozzle body is made by an additive manufacturing method.
7. A fuel injector as claimed in claim 1 or 3, characterized in that: the middle section heat insulation layer and the head heat insulation layer are vacuum heat insulation layers.
8. A fuel injector as claimed in claim 1 or 3, characterized in that: the middle section heat insulation layer and the head heat insulation layer are air heat insulation layers.
9. A fuel injector as claimed in claim 1 or 3, characterized in that: the thickness of interlude insulating layer with the head insulating layer is 0.5 ~ 1.5 mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010988344.3A CN112050253B (en) | 2020-09-18 | 2020-09-18 | Multiple thermal-insulated fuel nozzle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010988344.3A CN112050253B (en) | 2020-09-18 | 2020-09-18 | Multiple thermal-insulated fuel nozzle |
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| CN112050253A true CN112050253A (en) | 2020-12-08 |
| CN112050253B CN112050253B (en) | 2022-04-22 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114753932A (en) * | 2021-01-08 | 2022-07-15 | 中国航发商用航空发动机有限责任公司 | Oil collecting ring, fuel nozzle, combustion chamber, gas turbine engine and thermal protection method |
| CN114811656A (en) * | 2022-05-19 | 2022-07-29 | 上海和兰透平动力技术有限公司 | Fuel nozzle |
| CN115653759A (en) * | 2022-10-13 | 2023-01-31 | 中国航发四川燃气涡轮研究院 | Afterburner oil supply system based on flow distribution and control flow design method |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2865860Y (en) * | 2005-08-30 | 2007-02-07 | 宝山钢铁股份有限公司 | Supersonic nozzle for cold spraying |
| US20100071666A1 (en) * | 2008-09-19 | 2010-03-25 | Woodward Governor Company | Thermal Protection For Fuel Injectors |
| US20100186417A1 (en) * | 2007-07-10 | 2010-07-29 | Malte Blomeyer | Use of inert gases for shielding oxidizer and fuel |
| CN102563705A (en) * | 2012-02-15 | 2012-07-11 | 中国人民解放军国防科学技术大学 | Direct-flow fuel nozzle capable of preventing carbon deposit |
| CN104713128A (en) * | 2013-12-12 | 2015-06-17 | 中航商用航空发动机有限责任公司 | Nozzle rod part, fuel nozzle and aero-engine gas turbine |
| CN105042638A (en) * | 2015-06-25 | 2015-11-11 | 中国科学院工程热物理研究所 | Two-oil-way three-air-way multi-rotational-flow air atomizing nozzle structure |
| CN205279156U (en) * | 2015-12-14 | 2016-06-01 | 中国燃气涡轮研究院 | Hot protective structure of nozzle head |
| EP3062021A1 (en) * | 2015-02-27 | 2016-08-31 | United Technologies Corporation | Line replaceable fuel nozzle apparatus, system and method |
| CN107741030A (en) * | 2017-09-18 | 2018-02-27 | 北京航空航天大学 | A kind of blade injection low emission combustor head with cooling structure |
| CN210153864U (en) * | 2019-06-19 | 2020-03-17 | 中国科学院工程热物理研究所 | Dual-fuel nozzle |
| CN110953603A (en) * | 2019-12-05 | 2020-04-03 | 中国航发四川燃气涡轮研究院 | Multi-oil-path fuel oil spraying device suitable for radial grading main combustion chamber |
-
2020
- 2020-09-18 CN CN202010988344.3A patent/CN112050253B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2865860Y (en) * | 2005-08-30 | 2007-02-07 | 宝山钢铁股份有限公司 | Supersonic nozzle for cold spraying |
| US20100186417A1 (en) * | 2007-07-10 | 2010-07-29 | Malte Blomeyer | Use of inert gases for shielding oxidizer and fuel |
| US20100071666A1 (en) * | 2008-09-19 | 2010-03-25 | Woodward Governor Company | Thermal Protection For Fuel Injectors |
| CN102563705A (en) * | 2012-02-15 | 2012-07-11 | 中国人民解放军国防科学技术大学 | Direct-flow fuel nozzle capable of preventing carbon deposit |
| CN104713128A (en) * | 2013-12-12 | 2015-06-17 | 中航商用航空发动机有限责任公司 | Nozzle rod part, fuel nozzle and aero-engine gas turbine |
| EP3062021A1 (en) * | 2015-02-27 | 2016-08-31 | United Technologies Corporation | Line replaceable fuel nozzle apparatus, system and method |
| CN105042638A (en) * | 2015-06-25 | 2015-11-11 | 中国科学院工程热物理研究所 | Two-oil-way three-air-way multi-rotational-flow air atomizing nozzle structure |
| CN205279156U (en) * | 2015-12-14 | 2016-06-01 | 中国燃气涡轮研究院 | Hot protective structure of nozzle head |
| CN107741030A (en) * | 2017-09-18 | 2018-02-27 | 北京航空航天大学 | A kind of blade injection low emission combustor head with cooling structure |
| CN210153864U (en) * | 2019-06-19 | 2020-03-17 | 中国科学院工程热物理研究所 | Dual-fuel nozzle |
| CN110953603A (en) * | 2019-12-05 | 2020-04-03 | 中国航发四川燃气涡轮研究院 | Multi-oil-path fuel oil spraying device suitable for radial grading main combustion chamber |
Non-Patent Citations (1)
| Title |
|---|
| 黄义勇: "航空发动机主燃油喷嘴热防护设计技术研究", 《中国优秀博硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114753932A (en) * | 2021-01-08 | 2022-07-15 | 中国航发商用航空发动机有限责任公司 | Oil collecting ring, fuel nozzle, combustion chamber, gas turbine engine and thermal protection method |
| CN114811656A (en) * | 2022-05-19 | 2022-07-29 | 上海和兰透平动力技术有限公司 | Fuel nozzle |
| CN115653759A (en) * | 2022-10-13 | 2023-01-31 | 中国航发四川燃气涡轮研究院 | Afterburner oil supply system based on flow distribution and control flow design method |
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|---|---|
| CN112050253B (en) | 2022-04-22 |
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