RU2014134013A - METHOD FOR DETERMINING THE PERIODICITY OF CONTROL OF PARTS FOR THE AVIATION GAS-TURBINE ENGINE DURING OPERATION AT ITS TECHNICAL CONDITION - Google Patents
METHOD FOR DETERMINING THE PERIODICITY OF CONTROL OF PARTS FOR THE AVIATION GAS-TURBINE ENGINE DURING OPERATION AT ITS TECHNICAL CONDITION Download PDFInfo
- Publication number
- RU2014134013A RU2014134013A RU2014134013A RU2014134013A RU2014134013A RU 2014134013 A RU2014134013 A RU 2014134013A RU 2014134013 A RU2014134013 A RU 2014134013A RU 2014134013 A RU2014134013 A RU 2014134013A RU 2014134013 A RU2014134013 A RU 2014134013A
- Authority
- RU
- Russia
- Prior art keywords
- crack
- cycle
- parts
- engine
- technical condition
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract 7
- 238000009659 non-destructive testing Methods 0.000 claims abstract 6
- 238000001514 detection method Methods 0.000 claims abstract 4
- 238000012360 testing method Methods 0.000 claims abstract 4
- 238000007689 inspection Methods 0.000 claims abstract 2
- 230000003313 weakening effect Effects 0.000 claims abstract 2
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Testing Of Engines (AREA)
Abstract
Способ определения периодичности контроля деталей авиационного двигателя при эксплуатации по его техническому состоянию, включающий определение предельно допустимого значения повреждаемости основных деталей двигателя, при этом в качестве параметра, характеризующего повреждаемость детали двигателя, используют длину трещины, развивающуюся в зоне наибольшей концентрации напряжений при эксплуатации двигателя, в случае обнаружения трещины при контроле с помощью метода неразрушающего контроля эксплуатацию двигателя прекращают, отличающийся тем, что предварительно определяют зону наибольшей концентрации напряжений, искусственным способом наносят надрез,.. имитирующий трещину, ослабляющую деталь в плоскости, перпендикулярной направлению максимальных главных напряжений, производят нагружение детали ускоренным циклом с контролем трещины методом неразрушающего контроля, после обнаружения трещины цикл изменяют на цикл, соответствующий эксплуатационному, и продолжают испытание с ростом трещины до допустимого значения, при котором сохраняется несущая способность детали, далее устанавливают периодичность контроля при эксплуатации по техническому состоянию, соответствующую не более половины наработки между обнаружением трещины неразрушающим методом контроля и достижением ею предельно допустимого значения.A method for determining the frequency of control of parts of an aircraft engine during operation according to its technical condition, including determining the maximum allowable value of damage to the main engine parts, and the crack length developing in the zone of the highest stress concentration during engine operation is used as a parameter characterizing damage to the engine parts, in in case of crack detection during testing using the non-destructive testing method, engine operation is stopped, excellent In that they preliminarily determine the zone of the highest concentration of stresses, an incision is made artificially, simulating a crack, weakening the part in a plane perpendicular to the direction of the maximum principal stresses, loading the part with an accelerated cycle with crack control by non-destructive testing, after the crack is detected, the cycle is changed to the cycle corresponding to the operational cycle and continue testing with crack growth to an acceptable value at which the load bearing capacity is maintained hoists, then establish the frequency of inspection during operation according to the technical condition, corresponding to no more than half the time between the detection of a crack by the non-destructive testing method and its achievement of the maximum permissible value.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2014134013A RU2618145C2 (en) | 2014-08-19 | 2014-08-19 | Method for inspection intervals determination for aero-derivative gas turbine engine parts in case of operation according to its technical condition |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2014134013A RU2618145C2 (en) | 2014-08-19 | 2014-08-19 | Method for inspection intervals determination for aero-derivative gas turbine engine parts in case of operation according to its technical condition |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2014134013A true RU2014134013A (en) | 2016-03-20 |
| RU2618145C2 RU2618145C2 (en) | 2017-05-02 |
Family
ID=55530600
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2014134013A RU2618145C2 (en) | 2014-08-19 | 2014-08-19 | Method for inspection intervals determination for aero-derivative gas turbine engine parts in case of operation according to its technical condition |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2618145C2 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2669432C1 (en) * | 2017-08-24 | 2018-10-11 | Публичное Акционерное Общество "Одк-Сатурн" | Method for determining periodicity gas turbine engine part control |
| RU2721514C1 (en) * | 2019-04-17 | 2020-05-19 | Евгения Викторовна Георгиевская | Method for evaluation of residual life of hydraulic turbine impeller at beyond design basis of operation |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7020595B1 (en) * | 1999-11-26 | 2006-03-28 | General Electric Company | Methods and apparatus for model based diagnostics |
| RU2236671C1 (en) * | 2003-04-14 | 2004-09-20 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" | Method of operation of aircraft gas-turbine engine according to its technical state |
| DE602004012547T2 (en) * | 2004-07-19 | 2009-05-07 | Techspace Aero, Milmort | Test facility for the development of a jet engine |
| RU2308014C2 (en) * | 2005-08-16 | 2007-10-10 | Открытое акционерное общество Конструкторское-производственное предприятие "Авиамотор" | Method of operating the engine |
| RU2374614C2 (en) * | 2007-04-11 | 2009-11-27 | Открытое акционерное общество "Московское машиностроительное предприятие им. В.В. Чернышева" | Safe operation of aircraft gas turbine engine |
| RU2439527C2 (en) * | 2010-03-23 | 2012-01-10 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Method of operating aircraft gas turbine engine according to its technical state |
-
2014
- 2014-08-19 RU RU2014134013A patent/RU2618145C2/en active
Also Published As
| Publication number | Publication date |
|---|---|
| RU2618145C2 (en) | 2017-05-02 |
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