CN101676536B - Elastic mounting flange used for combustion gas turbine engine - Google Patents

Elastic mounting flange used for combustion gas turbine engine Download PDF

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Publication number
CN101676536B
CN101676536B CN 200810013242 CN200810013242A CN101676536B CN 101676536 B CN101676536 B CN 101676536B CN 200810013242 CN200810013242 CN 200810013242 CN 200810013242 A CN200810013242 A CN 200810013242A CN 101676536 B CN101676536 B CN 101676536B
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CN
China
Prior art keywords
annular component
gas turbine
turbine engine
elastic mounting
mounting flange
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
CN 200810013242
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Chinese (zh)
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CN101676536A (en
Inventor
陈亮
吴赛锋
金美子
尹家录
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AVIC Shenyang Engine Design and Research Institute
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AVIC Shenyang Engine Design and Research Institute
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Filing date
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Application filed by AVIC Shenyang Engine Design and Research Institute filed Critical AVIC Shenyang Engine Design and Research Institute
Priority to CN 200810013242 priority Critical patent/CN101676536B/en
Publication of CN101676536A publication Critical patent/CN101676536A/en
Application granted granted Critical
Publication of CN101676536B publication Critical patent/CN101676536B/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Abstract

The present invention provides an elastic mounting flange used for a combustion gas turbine engine, which is characterized in that: an annular member 1 is arranged between two pieces of flanges, the annular member 1 fixedly connects with two pieces of flanges 2 and shows staggered distribution. The elastic mounting flange has advantages in that: when pipelines on two sides of flanges have uneven thermal expansion, the expanded stress is transferred to the annular member through a fixing connection position of the annular member and two sides of the flanges, further, the annular member generates an elastic deformation for absorbing stress, which can prevent a connection position of the flange and the pipeline from being stress destroyed.

Description

A kind of elastic mounting flange for gas turbine engine
Technical field
The invention belongs to the gas turbine engine field.
Background technique
When the hot combustion gas of gas turbine engine is flowed in stream, can cause stream outer wall (casing) to produce thermal expansion.As shown in Figure 1, when two sections outer wall casings were in different structures, the suffered temperature of outer wall casing will be different.The heat combustion flow blast tube that outer wall casing A forms of flowing through arrives the formed stream of outer wall casing B.Obviously the temperature of outer wall casing A will be higher than outer wall casing B.Can produce thermal expansion because object is heated, thermal expansion is directly proportional with the situation of being heated.The thermal expansion of outer wall casing A will be higher than outer wall casing B like this, and the mounting flange, the attachment bolt place that carry out at outer wall outer wall casing A and outer wall casing B produce stress.When stress is excessive, can cause the permanent deformation of mounting flange or the fracture of connection stud.
Summary of the invention
The purpose of this invention is to provide a kind of elastic mounting flange for gas turbine engine.
The invention provides a kind of elastic mounting flange for gas turbine engine, annular component 1 is installed between two flange plate 2, annular component 1 is fixedly connected with two flange plate 2 respectively and the joint is interspersed, flange plate 2 internal diameters that the internal diameter of described annular component 1 compares go out greatly 0~5mm, the little 0~5mm of flange plate 2 external diameters that external diameter compares.
Elastic mounting flange for gas turbine engine provided by the invention adopts the pin 3 that is interspersed at same circumference respectively annular component 1 to be fixedly connected with two flange plate 2.
Elastic mounting flange for gas turbine engine provided by the invention adopts connecting bolt 4 that flange plate 2, annular component 1 are fixedly connected with, and the aperture that is positioned at the connecting bolt on the flange plate 2 is slightly larger than the diameter of bolt.
Elastic mounting flange for gas turbine engine provided by the invention, the material of described pin 3, connecting bolt 4, annular component 1 adopts heat-resistance stainless steel or refractory alloy.According to practical structures, the external diameter of elastic ring exists
Figure DEST_PATH_G200810013242901D00011
500mm~
Figure DEST_PATH_G200810013242901D00012
2000mm, thickness 8mm~20mm pin size exists
Figure DEST_PATH_G200810013242901D00013
6mm~
Figure DEST_PATH_G200810013242901D00014
20mm.
The invention has the advantages that: when the thermal expansion of flange both sides pipeline is uneven; the stress that expands is passed to annular component by annular component and fixed connection place, flange both sides; and then annular component produces resiliently deformable and absorbed stress, and protection flange and pipeline junction can not produce stress rupture.
Description of drawings
The schematic representation of the mounting flange joint of Fig. 1 conventional gas turbine motor
Fig. 2 is with the one-sided schematic representation of the mounting flange of annular component
Fig. 3 is with the one-sided schematic representation of the mounting flange of annular component
Fig. 4 pin distribution schematic diagram
Embodiment
A kind of elastic mounting flange for gas turbine engine, annular component 1 is installed between flange plate 2, material is refractory alloy GH3030, thickness is 10mm, and than the large 3mm of internal diameter of flange plate, external diameter is than the little 4mm of external diameter of flange plate respectively for internal diameter, annular component 1 is fixedly connected with two flange plate, 2 usefulness pins 3 respectively, see Fig. 2, Fig. 3, wherein pin 3 adopts refractory alloy GH4033 material, diameter 12mm.Pin 3 is seen Fig. 4 in the distribution situation of flange plate 2, and wherein the black circles representative connects annular component 1 and the pin of left side flange plate, the pin that the white circle representative is connected annular component 1 and right side flange plate.Adopt connecting bolt 4 that flange plate 2, annular component 1 are fixedly connected with, the binder bolt material is refractory alloy GH4033, and specification is M12.And the aperture that is positioned at the connecting bolt 4 on flange plate 2, the annular component is
Figure DEST_PATH_G200810013242901D00021
14mm.
Be applied on certain gas turbine, use experience shows that this arrangement works is reliable, meets design requirement, and can mechanically be widely used the similar of other model.

Claims (3)

1. elastic mounting flange that is used for gas turbine engine, it is characterized in that: annular component (1) is installed between two flange plate (2), flange plate (2) internal diameter that the internal diameter of described annular component (1) compares goes out greatly 0 ~ 5mm, the little 0 ~ 5mm of the flange plate that external diameter compares (2) external diameter; Pin on same circumference (3) is fixedly connected with annular component (1) with two flange plate (2), the pin (3) that connects respectively annular component (1) and left and right sides flange plate (2) is interspersed, and described annular component (1) is a kind of member of elastically deformable.
2. according to the elastic mounting flange for gas turbine engine claimed in claim 1, it is characterized in that: the material of described pin (3), annular component (1) adopts heat-resistance stainless steel or refractory alloy.
3. according to claim 1 or 2 described elastic mounting flanges for gas turbine engine, it is characterized in that: the thickness of described annular component (1) is 8mm~20mm.
CN 200810013242 2008-09-18 2008-09-18 Elastic mounting flange used for combustion gas turbine engine Expired - Fee Related CN101676536B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN 200810013242 CN101676536B (en) 2008-09-18 2008-09-18 Elastic mounting flange used for combustion gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN 200810013242 CN101676536B (en) 2008-09-18 2008-09-18 Elastic mounting flange used for combustion gas turbine engine

Publications (2)

Publication Number Publication Date
CN101676536A CN101676536A (en) 2010-03-24
CN101676536B true CN101676536B (en) 2013-04-24

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN 200810013242 Expired - Fee Related CN101676536B (en) 2008-09-18 2008-09-18 Elastic mounting flange used for combustion gas turbine engine

Country Status (1)

Country Link
CN (1) CN101676536B (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105135476A (en) * 2015-09-17 2015-12-09 中国航空工业集团公司沈阳发动机设计研究所 Lining assembly

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4815933A (en) * 1987-11-13 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Nozzle flange attachment and sealing arrangement
US6364606B1 (en) * 2000-11-08 2002-04-02 Allison Advanced Development Company High temperature capable flange
EP1439282A1 (en) * 2003-01-16 2004-07-21 Snecma Moteurs Device for mounting an annular flask at a radial side of a rotor
CN201187944Y (en) * 2007-11-13 2009-01-28 四川龙蟒集团有限责任公司 Conveying device of high temperature direct reduced iron

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4815933A (en) * 1987-11-13 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Nozzle flange attachment and sealing arrangement
US6364606B1 (en) * 2000-11-08 2002-04-02 Allison Advanced Development Company High temperature capable flange
EP1439282A1 (en) * 2003-01-16 2004-07-21 Snecma Moteurs Device for mounting an annular flask at a radial side of a rotor
CN201187944Y (en) * 2007-11-13 2009-01-28 四川龙蟒集团有限责任公司 Conveying device of high temperature direct reduced iron

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