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CN102425497B - Gas intake cone fixation structure of gas turbine engine - Google Patents

Gas intake cone fixation structure of gas turbine engine Download PDF

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Publication number
CN102425497B
CN102425497B CN2011104033195A CN201110403319A CN102425497B CN 102425497 B CN102425497 B CN 102425497B CN 2011104033195 A CN2011104033195 A CN 2011104033195A CN 201110403319 A CN201110403319 A CN 201110403319A CN 102425497 B CN102425497 B CN 102425497B
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intake cone
fixed
cone
intake
fixing
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Expired - Fee Related
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CN102425497A (en
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宋满祥
潘宁民
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Beihang University
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Beihang University
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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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

本发明公开了一种燃气涡轮发动机进气锥的固定结构，其特征在于它由进气锥锥体、进气锥联接环、进气锥定位销钉、波纹弹簧以及压气机盘固定翻边组成。进气锥联接环通过螺钉固定在进气锥锥体上，进气锥定位销钉固定在进气锥锥体上。压气机盘固定翻边由进气锥固定环上的缺口处旋入进气锥连接环槽内并由槽内的波纹弹簧压紧，定位销钉插入压气机盘上的销钉孔中。本发明可以方便快捷的固定进气锥，有效的减轻进气锥拆装时的工作量；同时消除了传统固定结构进气锥上的螺钉安装孔对发动机气动性能的影响。

The invention discloses a gas turbine engine intake cone fixing structure, which is characterized in that it is composed of an intake cone body, an intake cone coupling ring, an intake cone positioning pin, a corrugated spring and a compressor disk fixing flange. The intake cone connecting ring is fixed on the intake cone by screws, and the positioning pin of the intake cone is fixed on the intake cone. The fixed flange of the compressor disk is screwed into the groove of the inlet cone connecting ring by the notch on the fixed ring of the inlet cone and pressed tightly by the corrugated spring in the groove, and the positioning pin is inserted into the pin hole on the compressor disk. The invention can fix the intake cone conveniently and quickly, effectively reducing the workload when disassembling and assembling the intake cone; meanwhile, it eliminates the influence of the screw installation hole on the intake cone of the traditional fixed structure on the aerodynamic performance of the engine.

Description

燃气涡轮发动机进气锥固定结构Gas turbine engine intake cone fixing structure

技术领域 technical field

本发明涉及一种燃气涡轮发动机进气锥固定结构，属于燃气涡轮发动机结构设计技术领域。The invention relates to a gas turbine engine intake cone fixing structure, which belongs to the technical field of gas turbine engine structure design.

背景技术 Background technique

进气锥是燃气涡轮发动机压气机进气装置的重要组成部分，发动机前方空气通过进气锥的导向后进入压气机内。燃气涡轮发动机进气锥传统的安装和固定方法如图1所示，进气锥为分体式结构，由进气锥前段1、进气锥中段2、进气锥后段3组成，进气锥各段通过螺钉连接在一起形成一锥形筒，最后通过螺钉连接固定在压气机盘4上。如上所述，传统固定结构将进气锥分为几段安装，而且固定螺钉数量较多，装配时工作量大，并且进气锥上的螺钉安装孔会对气动性能产生影响。The intake cone is an important part of the gas turbine engine compressor intake device. The air in front of the engine enters the compressor after being guided by the intake cone. The traditional installation and fixing method of the gas turbine engine intake cone is shown in Figure 1. The intake cone is a split structure, consisting of the front section 1 of the intake cone, the middle section 2 of the intake cone, and the rear section 3 of the intake cone. Each section is connected together by screws to form a cone, and finally fixed on the compressor disc 4 by screws. As mentioned above, the traditional fixing structure divides the intake cone into several sections for installation, and the number of fixing screws is large, which requires a lot of work during assembly, and the screw mounting holes on the intake cone will affect the aerodynamic performance.

发明内容 Contents of the invention

本发明的内容是提供一种燃气涡轮发动机进气锥固定结构，可以更方便的固定进气锥，有效的减轻进气锥拆装时的工作量；同时消除了传统固定结构进气锥上的螺钉安装孔对发动机气动性能的影响。The content of the present invention is to provide a gas turbine engine intake cone fixing structure, which can fix the intake cone more conveniently, effectively reduce the workload when disassembling the intake cone; Effect of screw mounting holes on engine aerodynamic performance.

为实现上述目的，本发明采用如下技术方案：一种燃气涡轮发动机进气锥固定结构，其特征在于：该结构包括进气锥锥体5、进气锥联接环6、固定螺钉7、进气锥定位销钉8、弹簧9、波纹弹簧10以及压气机盘固定翻边11，该压气机盘固定翻边上设有固定边销钉孔12，其结构如图2、图3所示。In order to achieve the above object, the present invention adopts the following technical scheme: a gas turbine engine intake cone fixing structure, characterized in that: the structure includes an intake cone body 5, an intake cone coupling ring 6, a fixing screw 7, an intake Cone positioning pin 8, spring 9, corrugated spring 10 and compressor disk fixed flange 11, this compressor disk fixed flange is provided with fixed edge pin hole 12, its structure as shown in Figure 2, Figure 3.

其中，所述的进气锥联接环6上设有固定环槽61及螺孔。Wherein, the air intake cone coupling ring 6 is provided with a fixing ring groove 61 and screw holes.

其中，所述的压气机盘固定翻边为一圆盘状结构，沿圆周设有可卡置入固定环槽61内的凸齿，该凸齿上设有固定边销钉孔12。Wherein, the fixed flanging of the compressor disk is a disc-shaped structure, and there are convex teeth that can be inserted into the fixed ring groove 61 along the circumference, and the fixed edge pin holes 12 are provided on the convex teeth.

进气锥联接环6通过螺孔及固定螺钉7固定在进气锥锥体5上，进气锥定位销钉8由弹簧9固定在进气锥锥体5上。压气机盘固定翻边11由进气锥联接环6上的缺口处旋入固定环槽61内，并由设置于固定环槽61内的波纹弹簧10压紧。进气锥定位销钉8插入固定边销钉孔12中。The intake cone coupling ring 6 is fixed on the intake cone 5 through screw holes and fixing screws 7, and the intake cone positioning pin 8 is fixed on the intake cone 5 by a spring 9. The fixed flange 11 of the compressor disk is screwed into the fixed ring groove 61 by the notch on the intake cone coupling ring 6, and is compressed by the corrugated spring 10 arranged in the fixed ring groove 61. The air intake cone positioning pin 8 is inserted in the pin hole 12 of the fixed side.

其中，所述的压气机固定翻边与压气机盘为一体式结构。Wherein, the fixed flange of the compressor and the compressor disk are of an integrated structure.

本发明一种燃气涡轮发动机进气锥固定结构，其优点在于：A gas turbine engine intake cone fixing structure of the present invention has the advantages of:

1、结构简单，工艺容易实施。1. The structure is simple and the process is easy to implement.

2、安装拆卸方便，减轻拆装工作量。2. Easy installation and disassembly, reducing the workload of disassembly and assembly.

3、进气锥锥体为一整体结构件，避免了锥体分段安装造成的气动损失，同时减少了结构件数量及结构重量。3. The intake cone is an integral structural part, which avoids the aerodynamic loss caused by the segmental installation of the cone, and reduces the number of structural parts and the weight of the structure.

4、通过进气锥联接环与压气机盘固定翻边相配合进行进气锥的轴向固定，通过销钉与压气机盘上销钉孔的配合进行进气锥的周向定位。5、压气机盘固定翻边为本发明所特制的一个部件。固定翻边可以单独加工制造后用螺钉固定到压气机盘上，也可以将压气机盘固定翻边与压气机盘制成一体的。推荐将固定翻边与压气机盘制成一体的可以减少零件数量。4. The axial fixation of the intake cone is carried out through the cooperation of the connection ring of the intake cone and the fixed flange of the compressor disc, and the circumferential positioning of the intake cone is carried out through the cooperation of the pins and the pin holes on the compressor disc. 5. The fixed flanging of the compressor disk is a specially made part of the present invention. The fixed flanging can be processed and manufactured separately and fixed to the compressor disk with screws, or the fixed flange of the compressor disk can be integrated with the compressor disk. It is recommended to integrate the fixed flange with the compressor disc to reduce the number of parts.

附图说明 Description of drawings

图1所示为现有技术中燃气涡轮发动机进气锥固定结构；Fig. 1 shows the gas turbine engine intake cone fixing structure in the prior art;

图2所示为本发明中进气锥组件的结构图；Fig. 2 shows the structural diagram of the intake cone assembly in the present invention;

图3所示为图2的局部放大图；Figure 3 is a partial enlarged view of Figure 2;

图4所示为本发明中进气锥连接环的结构图；Fig. 4 shows the structural diagram of the air inlet cone connecting ring in the present invention;

图5所示为本发明中压气机盘翻边的结构图(固定翻边与压气机盘制成一体式结构)；Fig. 5 shows the structural diagram of the flange of the compressor disk in the present invention (the fixed flange and the compressor disk are made into an integrated structure);

图6所示为本发明的进气锥固定结构图；Fig. 6 shows the fixed structure diagram of the intake cone of the present invention;

图7所示为图6的局部放大图。FIG. 7 is a partially enlarged view of FIG. 6 .

图中具体标号如下：The specific labels in the figure are as follows:

1、进气锥前段  2、进气锥中段  3、进气锥后段  4、压气机盘5、进气锥锥体  6、进气锥联接环  61、固定环槽7、固定螺钉  8、进气锥定位销钉  9、弹簧10、波纹弹簧  11、压气机盘固定翻边  12、固定边销钉孔1. Front section of intake cone 2. Middle section of intake cone 3. Rear section of intake cone 4. Compressor disc 5. Intake cone body 6. Intake cone coupling ring 61. Fixing ring groove 7. Fixing screw 8. Intake Air cone positioning pin 9, spring 10, corrugated spring 11, compressor disk fixed flange 12, fixed edge pin hole

具体实现方式Specific implementation

下面结合附图，对本发明的技术方案做进一步的说明。The technical solution of the present invention will be further described below in conjunction with the accompanying drawings.

本发明一种燃气涡轮发动机进气锥固定结构，该结构包括进气锥锥体5、进气锥联接环6、固定螺钉7、进气锥定位销钉8、弹簧9、波纹弹簧10以及压气机盘固定翻边11，该压气机盘固定翻边上设有固定边销钉孔12，其结构如图2、图3所示。The invention relates to a gas turbine engine intake cone fixing structure, which comprises an intake cone body 5, an intake cone coupling ring 6, a fixing screw 7, an intake cone positioning pin 8, a spring 9, a corrugated spring 10 and a compressor Disk fixed flanging 11, the compressor disk fixed flange is provided with fixed edge pin holes 12, its structure as shown in Figure 2, Figure 3.

如图4所示，进气锥联接环6上设有固定环槽61及螺孔。As shown in FIG. 4 , the intake cone coupling ring 6 is provided with a fixing ring groove 61 and a screw hole.

其中，所述的压气机盘固定翻边为一圆盘状结构，沿圆周设有可卡置入固定环槽61内的凸齿，该凸齿上设有固定边销钉孔12。如图5所示，压气机固定翻边与压气机盘为一体式结构。Wherein, the fixed flanging of the compressor disk is a disc-shaped structure, and there are convex teeth that can be inserted into the fixed ring groove 61 along the circumference, and the fixed edge pin holes 12 are provided on the convex teeth. As shown in Figure 5, the fixed flange of the compressor and the compressor disk are of an integrated structure.

进气锥联接环6通过螺孔及固定螺钉7固定在进气锥锥体5上，进气锥定位销钉8由弹簧9固定在进气锥锥体5上。压气机盘固定翻边11由进气锥联接环6上的缺口处旋入固定环槽61内，并由设置于固定环槽61内的波纹弹簧10压紧。进气锥定位销钉8插入固定边销钉孔12中，如图6、7所示，拆卸过程与安装过程相反。The intake cone coupling ring 6 is fixed on the intake cone 5 through screw holes and fixing screws 7, and the intake cone positioning pin 8 is fixed on the intake cone 5 by a spring 9. The fixed flange 11 of the compressor disk is screwed into the fixed ring groove 61 by the notch on the intake cone coupling ring 6, and is compressed by the corrugated spring 10 arranged in the fixed ring groove 61. The positioning pin 8 of the intake cone is inserted into the pin hole 12 of the fixed side, as shown in Figures 6 and 7, the disassembly process is opposite to the installation process.

Claims (2)

1.一种燃气涡轮发动机进气锥固定结构，其特征在于：该结构包括进气锥锥体（5）、进气锥联接环（6）、固定螺钉（7）、进气锥定位销钉（8）、弹簧（9）、波纹弹簧（10）以及压气机盘固定翻边（11），该压气机盘固定翻边上设有固定边销钉孔（12），所述的进气锥联接环（6）上设有固定环槽（61）及螺孔，所述的压气机盘固定翻边为一圆盘状结构，沿圆周设有可卡置入固定环槽（61）内的凸齿，该凸齿上设有固定边销钉孔（12）；1. A gas turbine engine intake cone fixing structure is characterized in that: the structure comprises an intake cone cone (5), an intake cone coupling ring (6), a fixing screw (7), an intake cone positioning pin ( 8), spring (9), corrugated spring (10) and compressor disk fixed flange (11), the fixed flange of the compressor disk is provided with fixed edge pin holes (12), and the inlet cone coupling ring (6) is provided with a fixed ring groove (61) and a screw hole, and the fixed flanging of the compressor disk is a disc-shaped structure, and there are convex teeth that can be inserted into the fixed ring groove (61) along the circumference , the convex tooth is provided with fixed side pin holes (12); 进气锥联接环（6）通过螺孔及固定螺钉（7）固定在进气锥锥体（5）上，进气锥定位销钉（8）由弹簧（9）固定在进气锥锥体（5）上，压气机盘固定翻边（11）由进气锥联接环（6）上的缺口处旋入固定环槽（61）内，并由设置于固定环槽（61）内的波纹弹簧（10）压紧，进气锥定位销钉（8）插入固定边销钉孔（12）中。The intake cone coupling ring (6) is fixed on the intake cone (5) through screw holes and fixing screws (7), and the intake cone positioning pin (8) is fixed on the intake cone ( 5), the compressor disc fixing flange (11) is screwed into the fixing ring groove (61) by the notch on the inlet cone coupling ring (6), and the corrugated spring installed in the fixing ring groove (61) (10) Press it tightly, insert the positioning pin (8) of the intake cone into the pin hole (12) of the fixed side. 2.根据权利要求1所述的燃气涡轮发动机进气锥固定结构，其特征在于：所述的压气机盘固定翻边（11）与压气机盘为一体式结构。2. The gas turbine engine intake cone fixing structure according to claim 1, characterized in that: the compressor disk fixing flange (11) is an integral structure with the compressor disk.
CN2011104033195A 2011-12-07 2011-12-07 Gas intake cone fixation structure of gas turbine engine Expired - Fee Related CN102425497B (en)

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CN104373160B (en) * 2014-10-09 2017-01-11 中国石油天然气集团公司 Air intake cone of flue gas turbine and flue gas turbine
CN106555675B (en) * 2015-09-30 2018-07-10 中国航发商用航空发动机有限责任公司 Fan inlet cone and aviation turbofan engine gas handling system
CN111577461B (en) * 2020-05-11 2021-08-17 中国航发沈阳发动机研究所 Cap mounting structure
CN112753788B (en) * 2021-01-15 2022-11-22 湖北小稀藤茶叶有限公司 Tea leaf baking machine with automatic overturning function

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EP2161431A2 (en) * 2008-09-03 2010-03-10 Rolls-Royce Deutschland Ltd & Co KG Inlet nose cone for an aircraft gas turbine powerplant
CN102227544A (en) * 2008-12-10 2011-10-26 斯奈克玛 Fan for a turbine engine including a balancing system with blind holes for housing bodies, and related turbine engine

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US5833435A (en) * 1996-12-24 1998-11-10 United Technologies Corporation Inlet nose cone assembly and method for repairing the assembly
DE102004018585A1 (en) * 2004-04-16 2005-12-01 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine engine inlet cone, has upper surface whose structure varies in axial direction such that surface applies force on inflowing particles, relative to rotation axis, so that particles are conducted radially outwards along trajectory
EP2161431A2 (en) * 2008-09-03 2010-03-10 Rolls-Royce Deutschland Ltd & Co KG Inlet nose cone for an aircraft gas turbine powerplant
CN102227544A (en) * 2008-12-10 2011-10-26 斯奈克玛 Fan for a turbine engine including a balancing system with blind holes for housing bodies, and related turbine engine

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