CN116050193B - Damping hole layout method for improving high cycle fatigue life of elastic ring - Google Patents

Damping hole layout method for improving high cycle fatigue life of elastic ring Download PDF

Info

Publication number
CN116050193B
CN116050193B CN202310340746.6A CN202310340746A CN116050193B CN 116050193 B CN116050193 B CN 116050193B CN 202310340746 A CN202310340746 A CN 202310340746A CN 116050193 B CN116050193 B CN 116050193B
Authority
CN
China
Prior art keywords
damping
elastic ring
circumferential
ring
layout area
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.)
Active
Application number
CN202310340746.6A
Other languages
Chinese (zh)
Other versions
CN116050193A (en
Inventor
曾瑶
张少平
石斌
庞燕龙
陈亮
高雄兵
张琼
李光辉
李盛翔
江志敏
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC Sichuan Gas Turbine Research Institute
Original Assignee
AECC Sichuan Gas Turbine Research Institute
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by AECC Sichuan Gas Turbine Research Institute filed Critical AECC Sichuan Gas Turbine Research Institute
Priority to CN202310340746.6A priority Critical patent/CN116050193B/en
Publication of CN116050193A publication Critical patent/CN116050193A/en
Application granted granted Critical
Publication of CN116050193B publication Critical patent/CN116050193B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Theoretical Computer Science (AREA)
  • Computer Hardware Design (AREA)
  • Evolutionary Computation (AREA)
  • Geometry (AREA)
  • General Engineering & Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Springs (AREA)

Abstract

The invention provides a damping hole layout method for prolonging the high cycle fatigue life of an elastic ring, which comprises the steps of obtaining the total number of damping holes on a ring section between an upper outer boss and an adjacent inner boss of the elastic ring based on the damping characteristic of the elastic ring; acquiring a circumferential layout area of a damping hole on the ring segment; layout is carried out on the damping holes on the circumferential layout area; and calculating the coordinate position of each damping hole to complete the layout of the damping holes on the elastic ring. According to the method disclosed by the invention, on one hand, the damping Kong Kongbian stress can be met, the high cycle fatigue requirement can be met, and the problem of high cycle fatigue caused by tapping can be avoided; on the other hand, the average stress of the section caused by the open pores is avoided from being greatly reduced, and the strength reserve of the elastic ring is facilitated.

Description

Damping hole layout method for improving high cycle fatigue life of elastic ring
Technical Field
The invention belongs to the technical field of aeroengines, relates to a layout method of damping holes on a damper, and in particular relates to a layout method of damping holes for prolonging the high-cycle fatigue life of an elastic ring.
Background
Along with the design trend of high load and light weight of modern aero-engines, most of engine rotors adopt a soft shaft design, namely, the working rotation speed of the engine is higher than the critical rotation speed of the rotor, when the rotor approaches or passes through the critical rotation speed, the rotor and a supporting system can generate great vibration, and in order to control the vibration of the whole engine, the reliability of the engine is improved, and the vibration reduction design of a rotor system is a necessary means.
The elastic ring type extrusion oil film damper is characterized in that an elastic ring with a centering elastic supporting function is added on the basis of a traditional extrusion oil film damper (SFD), so that the characteristics of simple SFD structure and good vibration damping performance are fully exerted, and the problem of high nonlinearity of oil film rigidity is solved. The elastic ring is used as an important element, the common structural form is that inner and outer bosses are distributed alternately in the circumferential direction of the elastic ring section, damping holes are designed in the ring section between adjacent bosses and used for mutually transmitting lubricating oil in adjacent small oil cavities, and stable damping force is guaranteed to be provided.
At present, the research of the elastic ring is mainly focused on the research of dynamic characteristics, and the design of boss structural parameters of the elastic ring is focused on, so that the requirement of uniform layout is only provided for the distribution of damping holes, and the uniformity of pressure in a small oil cavity during working is ensured. However, in practice, when the damping holes on the elastic ring are distributed improperly, obvious stress concentration is caused, so that the high cycle fatigue life of the elastic ring is greatly reduced, and the durability and reliability of the engine are affected.
Disclosure of Invention
The invention provides a damping hole layout method for improving the high cycle fatigue life of an elastic ring, which is used for solving the fatigue problem caused by improper distribution of damping holes on the elastic ring.
The technical scheme for realizing the aim of the invention is as follows: a damping hole layout method for improving the high cycle fatigue life of an elastic ring comprises the following steps:
s1, acquiring total number of damping holes on a ring section between an outer boss and an adjacent inner boss on an elastic ring based on damping characteristics of the elastic ring;
s2, acquiring a circumferential layout area of the damping hole on the ring segment;
s3, distributing damping holes on the circumferential distribution area;
and S4, calculating the coordinate position of each damping hole to complete the layout of the damping holes on the elastic ring.
In one embodiment, in step S2, the area of the circumferential layout area is smaller than the area of the ring segments, in particular, the axial edges of the circumferential layout area are spaced from the axial edges of the ring segments.
In an optional embodiment, in step S2, the circumferential layout area is obtained according to the structural parameters and the material parameters of the elastic ring, and the circumferential layout area is specifically obtained according to the formula
Figure SMS_3
Calculating an acquisition, wherein->
Figure SMS_6
For circumferential layout area->
Figure SMS_8
The cycle number of the elastic ring is 10 7 Fatigue strength limit of the material at time->
Figure SMS_1
Is the tensile strength limit of the elastic ring material, +.>
Figure SMS_5
Is stress concentration coefficient->
Figure SMS_9
Reserve coefficients for high cycle fatigue strength, +.>
Figure SMS_10
Is the elastic modulus of the ring segment material +.>
Figure SMS_2
Is the thickness of the ring section->
Figure SMS_4
For the length of the ring segment->
Figure SMS_7
Clipping the gap for the elastic loop.
In one embodiment, in step S3, the damping holes in the circumferential layout area are laid out according to a dislocation distribution theory.
In one embodiment, in step S2, the total number of damping holes on the ring segment is an even number considering symmetry of the damping hole layout.
In one embodiment, in step S3, the theoretical basis formula is based on dislocation distribution
Figure SMS_11
、
Figure SMS_12
Layout is carried out on the damping holes on the circumferential layout area, wherein m is the number of rows which are arranged along the axial direction of the circumferential layout area, n is the number of columns which are arranged along the circumferential direction of the circumferential layout area, and +.>
Figure SMS_13
The total number of the damping holes on the ring section.
In an alternative embodiment, in step S4, the coordinate position of the orifice core of each orifice is formulated
Figure SMS_16
，/>
Figure SMS_17
Laying out damping holes in the circumferential layout area, wherein->
Figure SMS_20
For circumferential layout area->
Figure SMS_15
The sequence numbers of the damping holes are defined, and the sequence numbers from the outer boss of the elastic ring to the adjacent inner boss are sequentially numbered from small to large; />
Figure SMS_18
Is the center and the circumference of the damping holeCircumferential distance of the circumferential boundary of the layout area, +.>
Figure SMS_19
For the axial distance of the orifice core of the damping orifice from the axial boundary of the circumferential layout area, +.>
Figure SMS_21
Is the axial length of the elastic ring->
Figure SMS_14
The total number of the damping holes on the ring section.
Compared with the prior art, the invention has the beneficial effects that: according to the damping hole layout method for improving the high cycle fatigue life of the elastic ring, the range of the circumferential layout area of the damping hole layout is determined, so that the damping Kong Kongbian stress meets the high cycle fatigue requirement, the problem of high cycle fatigue caused by open pores is avoided, the problem of greatly reduced average stress of the section caused by open pores is avoided by the staggered layout method of the damping hole on the circumferential layout area, and the strength reserve of the elastic ring is facilitated.
The method of the invention is successfully applied to the distribution design of the damping holes of the elastic ring of a turbofan engine, and proved by verification, in the test of parts, the method passes through 2 multiplied by 10 7 And the high-cycle fatigue test and examination are carried out along with the complete machine, and the durable test and examination are completed.
Drawings
In order to more clearly illustrate the technical solution of the embodiments of the present invention, the drawings that are needed in the description of the embodiments will be briefly described.
FIG. 1 is a flow chart of a method for arranging damping holes for improving the high cycle fatigue life of an elastic ring according to the present invention.
Detailed Description
The invention will be further described with reference to specific embodiments, and advantages and features of the invention will become apparent from the description. These examples are merely exemplary and do not limit the scope of the invention in any way. It will be understood by those skilled in the art that various changes and substitutions of details and forms of the technical solution of the present invention may be made without departing from the spirit and scope of the present invention, but these changes and substitutions fall within the scope of the present invention.
The embodiment provides a damping hole layout method for improving the high cycle fatigue life of an elastic ring, which is shown in fig. 1, and comprises the following steps:
s1, acquiring total number of damping holes on a ring section between an outer boss and an adjacent inner boss on an elastic ring based on damping characteristics of the elastic ring;
s2, acquiring a circumferential layout area of the damping hole on the ring segment;
s3, distributing damping holes on the circumferential distribution area;
and S4, calculating the coordinate position of each damping hole to complete the layout of the damping holes on the elastic ring.
In one embodiment, a plurality of inner bosses are uniformly distributed on the inner circumferential wall of the elastic ring on the elastic ring, a plurality of outer bosses are uniformly distributed on the outer circumferential wall of the elastic ring, and the inner bosses and the outer bosses are distributed at intervals from the view of the circular section of the elastic ring. In this embodiment, the ring segment between two adjacent outer bosses is selected for stress analysis, the inner boss bears the pressure of the bearing, and the outer bosses are fixed on the stator member, which can be regarded as constraint. Meanwhile, because the span between two adjacent outer bosses of the elastic ring is smaller and the thickness of the elastic ring is far smaller than the radius of the elastic ring, the ring section between the two adjacent outer bosses can be regarded as a straight beam, two ends are fixedly supported, the middle inner boss of the ring section bears the bearing load of 2F, and because the ring section structure and the stress have symmetry relative to the inner boss, a stress simplified model is constructed by taking half of the symmetrical structure for analysis, namely, in the step S1, the ring section between the outer boss and the adjacent inner boss is used as an analysis section, and the circumferential layout area is calculated.
In one embodiment, in step S2, the area of the circumferential layout area is smaller than the area of the ring segments, in particular, the axial edges of the circumferential layout area are spaced from the axial edges of the ring segments.
In an alternative embodiment, according to structural parameters and material parameter analysis of the elastic ring, it can be known that the bending stress layout and the bending moment layout rule on the ring segment are consistent and are all linear layouts, so that the elastic ring allows the proportional relationship between the circumferential distribution area of the opening and the ring segment to be consistent with the stress, and the size of the circumferential layout area can be calculated.
Specifically, in step S2, the circumferential layout area is obtained according to the structural parameters and the material parameters of the elastic ring, and the circumferential layout area is specifically obtained according to the formula
Figure SMS_22
Calculating an acquisition, wherein->
Figure SMS_27
For circumferential layout area->
Figure SMS_30
The cycle number of the elastic ring is 10 7 Fatigue strength limit of the material at time->
Figure SMS_23
Is the tensile strength limit of the elastic ring material, +.>
Figure SMS_25
Is stress concentration coefficient->
Figure SMS_28
Reserve coefficients for high cycle fatigue strength, +.>
Figure SMS_31
Is the elastic modulus of the ring segment material +.>
Figure SMS_24
Is the thickness of the ring section->
Figure SMS_26
For the length of the ring segment->
Figure SMS_29
Clipping the gap for the elastic loop.
In one embodiment, when the damping holes are distributed on the circumferential distribution area, when a plurality of damping holes are distributed on the same circumferential position, the average stress of the cross section is larger when the actual width of the cross section is smaller, which is unfavorable for the strength storage of the elastic ring, so in the step S3, the damping holes on the circumferential distribution area are distributed according to the dislocation distribution theory.
Meanwhile, considering symmetry of the layout of the damping holes, in step S2, the total number of the damping holes on the ring segment is an even number.
Specifically, in the step S3, the theoretical basis formula is based on dislocation distribution
Figure SMS_32
、/>
Figure SMS_33
Layout is carried out on the damping holes on the circumferential layout area, wherein m is the number of rows which are arranged along the axial direction of the circumferential layout area, n is the number of columns which are arranged along the circumferential direction of the circumferential layout area, and +.>
Figure SMS_34
The total number of the damping holes on the ring section.
In an alternative embodiment, in step S4, the coordinate position of the orifice core of each orifice is formulated
Figure SMS_35
，/>
Figure SMS_39
Laying out damping holes in the circumferential layout area, wherein->
Figure SMS_41
For circumferential layout area->
Figure SMS_37
The sequence numbers of the damping holes are defined, and the sequence numbers from the outer boss of the elastic ring to the adjacent inner boss are sequentially numbered from small to large; />
Figure SMS_38
For the circumferential distance between the orifice core of the damping orifice and the circumferential boundary of the circumferential layout area, +.>
Figure SMS_40
For the axial distance of the orifice core of the damping orifice from the axial boundary of the circumferential layout area, +.>
Figure SMS_42
Is the axial length of the elastic ring->
Figure SMS_36
The total number of the damping holes on the ring section.
According to the damping hole layout method for improving the high cycle fatigue life of the elastic ring, the range of the circumferential layout area of the damping hole layout is determined, so that the damping Kong Kongbian stress meets the high cycle fatigue requirement, the problem of high cycle fatigue caused by open pores is avoided, the problem of greatly reduced average stress of the cross section caused by open pores is avoided by the staggered layout method of the damping hole on the circumferential layout area, and the strength reserve of the elastic ring is facilitated.
The method disclosed in the specific embodiment is successfully applied to the distribution design of the damping holes of the elastic ring of a certain turbofan engine, and is verified that in the test of parts, the damping holes pass through the damping holes of the elastic ring of the turbofan engine by 2 multiplied by 10 7 And the high-cycle fatigue test and examination are carried out along with the complete machine, and the durable test and examination are completed.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the invention.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.

Claims (4)

1. A damping hole layout method for improving the high cycle fatigue life of an elastic ring is characterized by comprising the following steps:
s1, acquiring total number of damping holes on a ring section between an outer boss and an adjacent inner boss on an elastic ring based on damping characteristics of the elastic ring;
s2, acquiring a circumferential layout area of the damping hole on the ring segment, wherein the circumferential layout area is according to a formula
Figure QLYQS_2
Calculating an acquisition, wherein->
Figure QLYQS_6
For circumferential layout area->
Figure QLYQS_7
The cycle number of the elastic ring is 10 7 Fatigue strength limit of the material at time->
Figure QLYQS_3
Is the tensile strength limit of the elastic ring material, +.>
Figure QLYQS_4
Is stress concentration coefficient->
Figure QLYQS_9
Reserve coefficients for high cycle fatigue strength, +.>
Figure QLYQS_10
Is the elastic modulus of the ring segment material +.>
Figure QLYQS_1
For the thickness of the ring segment,
Figure QLYQS_5
for the length of the ring segment->
Figure QLYQS_8
Clipping gap for elastic ring:
s3, distributing damping holes on the circumferential distribution area according to a dislocation distribution theory;
s4, calculating the coordinate position of each damping hole core to complete the layout of the damping holes on the elastic ring, wherein the coordinate position of each damping hole core adopts a formula
Figure QLYQS_12
，/>
Figure QLYQS_15
Calculated, wherein->
Figure QLYQS_17
For circumferential layout area->
Figure QLYQS_11
The sequence numbers of the damping holes are defined, and the sequence numbers from the outer boss of the elastic ring to the adjacent inner boss are sequentially numbered from small to large; />
Figure QLYQS_14
For the circumferential distance between the orifice core of the damping orifice and the circumferential boundary of the circumferential layout area, +.>
Figure QLYQS_16
For the axial distance of the orifice core of the damping orifice from the axial boundary of the circumferential layout area, +.>
Figure QLYQS_18
Is the axial length of the elastic ring->
Figure QLYQS_13
The total number of the damping holes on the ring section.
2. The method according to claim 1, wherein in step S2, the area of the circumferential layout area is smaller than the area of the ring segment.
3. The method according to claim 1, wherein in step S2, the total number of the damping holes in the ring segment is an even number.
4. The method for improving the high cycle fatigue life of an elastic ring according to claim 3, wherein in step S3, the theoretical basis formula of dislocation distribution is based
Figure QLYQS_19
、/>
Figure QLYQS_20
Layout is carried out on the damping holes on the circumferential layout area, wherein m is the number of rows which are arranged along the axial direction of the circumferential layout area, n is the number of columns which are arranged along the circumferential direction of the circumferential layout area, and +.>
Figure QLYQS_21
The total number of the damping holes on the ring section.
CN202310340746.6A 2023-04-03 2023-04-03 Damping hole layout method for improving high cycle fatigue life of elastic ring Active CN116050193B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310340746.6A CN116050193B (en) 2023-04-03 2023-04-03 Damping hole layout method for improving high cycle fatigue life of elastic ring

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310340746.6A CN116050193B (en) 2023-04-03 2023-04-03 Damping hole layout method for improving high cycle fatigue life of elastic ring

Publications (2)

Publication Number Publication Date
CN116050193A CN116050193A (en) 2023-05-02
CN116050193B true CN116050193B (en) 2023-06-30

Family

ID=86131693

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310340746.6A Active CN116050193B (en) 2023-04-03 2023-04-03 Damping hole layout method for improving high cycle fatigue life of elastic ring

Country Status (1)

Country Link
CN (1) CN116050193B (en)

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN204041122U (en) * 2014-08-15 2014-12-24 中国燃气涡轮研究院 A kind of frictional damping vibration damping structure of turbine blisk
US10487687B1 (en) * 2016-09-15 2019-11-26 United Technologies Corporation Gas turbine engine having a seal damper assembly
CN108131421A (en) * 2017-12-27 2018-06-08 哈尔滨广瀚燃气轮机有限公司 A kind of elastic ring squeeze film damper with special-shaped aperture
CN207661062U (en) * 2017-12-27 2018-07-27 哈尔滨广瀚燃气轮机有限公司 A kind of elastic ring squeeze film damper with special-shaped aperture
CN112487683B (en) * 2020-12-01 2022-08-16 北京航空航天大学 Structural member high-cycle fatigue life prediction method considering residual stress influence
CN114154362B (en) * 2021-10-20 2023-06-30 中国航发四川燃气涡轮研究院 Simulation evaluation method for damping characteristics of turbine blade edge plate based on energy dissipation
CN115165185A (en) * 2022-06-21 2022-10-11 西北核技术研究所 Curved surface explosive load distributed impulse calibration device
CN218628889U (en) * 2022-09-15 2023-03-14 中国航发四川燃气涡轮研究院 Fatigue life checking test platform for elastic ring type squeeze film damper

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
高阻尼黏弹性橡胶连梁阻尼器力学性能试验研究;王玉璋;潘鹏;邓开来;高田友和;何飞;;建筑结构学报(第03期);全文 *

Also Published As

Publication number Publication date
CN116050193A (en) 2023-05-02

Similar Documents

Publication Publication Date Title
RU2580447C2 (en) Blades system and appropriate gas turbine
US9850814B2 (en) Annular spring for a bearing assembly of a gas turbine engine
EP1586741A2 (en) Apparatus for damping vibrations of the stator vanes of a gas turbine engine
CN102187061B (en) Gas turbine
JP2013526672A (en) Exhaust gas turbocharger
ES2583756T3 (en) Blade arrangement for a turbomachine
US9194253B2 (en) Flexible rear bearing mounting, having an abutment, for a turbine engine
WO2014130332A1 (en) Gas turbine engine having a mistuned stage
US10190416B2 (en) Blade cascade for turbo machine
CN113227539B (en) Bladed rotor system and corresponding maintenance method
US20140169712A1 (en) Journal Bearing Device
CN116050193B (en) Damping hole layout method for improving high cycle fatigue life of elastic ring
US10584591B2 (en) Rotor with subset of blades having a cutout leading edge
EP3208421A1 (en) Turbine blade centroid shifting method and system
CN106499443A (en) Damping pin and turbogenerator
JP2015135076A (en) Seal structure for moving blades, moving blades, and rotary machine
JP6165841B2 (en) Stator blade ring and design method of stator blade ring for axial flow fluid machine
CN202493292U (en) Novel balanced structure of impeller of steam turbine
CN116127654A (en) Design method of damper simulation tester with elastic ring type extrusion oil film
CN114812938A (en) Indirect measurement method for dynamic balance of turbine rotor assembly
JP4475703B2 (en) High-load turbine blade arrangement
EP3097270B1 (en) Gas turbine engine inner case with non-integral vanes
RU151731U1 (en) LONG-LAST WORKING BLADE OF THE LAST STEPS OF A STEAM TURBINE
CN116090135B (en) Damper-rotor system response analysis method
CN117874930B (en) Rotor dynamics design method based on minimum equivalent stiffness

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant