EA201700153A1 - METHOD FOR MONITORING THE SURFACE OF A GAS TURBINE ENGINE BLADE - Google Patents
METHOD FOR MONITORING THE SURFACE OF A GAS TURBINE ENGINE BLADEInfo
- Publication number
- EA201700153A1 EA201700153A1 EA201700153A EA201700153A EA201700153A1 EA 201700153 A1 EA201700153 A1 EA 201700153A1 EA 201700153 A EA201700153 A EA 201700153A EA 201700153 A EA201700153 A EA 201700153A EA 201700153 A1 EA201700153 A1 EA 201700153A1
- Authority
- EA
- Eurasian Patent Office
- Prior art keywords
- roughness
- blade
- gte
- blades
- range
- Prior art date
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Изобретение относится к двигателестроению и может быть использовано для контроля поверхностей лопаток газотурбинных двигателей (ГТД). В процессе эксплуатации в результате высокотемпературного и эрозионного воздействия исходная шероховатость (высота неровностей) поверхности лопаток ГТД увеличивается в широких пределах, что приводит к увеличению удельного расхода топлива и снижению КПД ГТД. Во избежание этого при эксплуатации необходимо периодически осуществлять контроль состояния поверхности лопаток. Для оценки эксплуатационных свойств поверхностей лопаток ГТД используется усреднённая характеристика их шероховатости R. Однако одним и тем же средним значениям шероховатости могут соответствовать поверхности с кардинально различными свойствами, что говорит о недостаточности использования параметра Rв качестве единственного критерия отбраковки. Задачей изобретения является контроль процесса изнашивания лопатки ГТД не только по шероховатости, но и по величине субшероховатости её поверхностного слоя. Поставленная задача решается тем, что в способе контроля лопаток газотурбинного двигателя, включающем измерение геометрических параметров совокупности точек, расположенных вблизи основания, в середине и вблизи вершины лопатки на расстоянии 10, 50 и 90% от высоты лопатки соответственно, проверку отклонения величины параметра от диапазона пригодности и признание лопатки годной, если величина параметра находится внутри диапазона пригодности, или отбраковку лопатки, если величина параметра не находится внутри диапазона пригодности, согласно изобретению замеряется средняя высота неровностей субшероховатости Н на базовом участке 1×1 мкм (1000×1000 нм) и при H≤14 нм и шероховатости R=0,1-0,5 мкм лопатка считается пригодной для дальнейшей эксплуатации.The invention relates to engine and can be used to control the surfaces of the blades of gas turbine engines (GTE). During operation, as a result of high-temperature and erosion effects, the initial roughness (height of irregularities) of the surface of GTE blades increases over a wide range, which leads to an increase in specific fuel consumption and a decrease in the efficiency of the GTE. To avoid this, during operation, it is necessary to periodically monitor the condition of the surface of the blades. To assess the performance properties of the surfaces of GTE blades, an average characteristic of their roughness R is used. However, the same average roughness values can correspond to a surface with radically different properties, which indicates the insufficient use of the parameter R as the sole criterion of rejection. The objective of the invention is to control the process of wear of the GTE blade, not only in terms of roughness, but also in terms of the size of the sub-roughness of its surface layer. The task is solved by the fact that in the method of monitoring the blades of a gas turbine engine, including measuring the geometric parameters of a set of points located near the base, in the middle and near the top of the blade at a distance of 10, 50 and 90% of the height of the blade, respectively, checking the deviation of the parameter value from the suitability range and recognition of the blade as valid if the parameter value is within the range of suitability, or rejection of the blade, if the parameter value is not within the range of fitness, agree The invention measures the average height of the irregularities of the sub-roughness H in the base area 1 × 1 μm (1000 × 1000 nm) and at H ≤ 14 nm and roughness R = 0.1–0.5 μm, the blade is considered suitable for further operation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EA201700153A EA032992B1 (en) | 2016-12-21 | 2016-12-21 | Method for control of a gas turbine engine blade surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EA201700153A EA032992B1 (en) | 2016-12-21 | 2016-12-21 | Method for control of a gas turbine engine blade surface |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EA201700153A1 true EA201700153A1 (en) | 2018-06-29 |
| EA032992B1 EA032992B1 (en) | 2019-08-30 |
Family
ID=62684536
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EA201700153A EA032992B1 (en) | 2016-12-21 | 2016-12-21 | Method for control of a gas turbine engine blade surface |
Country Status (1)
| Country | Link |
|---|---|
| EA (1) | EA032992B1 (en) |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2889308B1 (en) * | 2005-07-28 | 2007-10-05 | Snecma | CONTROL OF TURBOMACHINE AUBES |
| WO2012097348A2 (en) * | 2011-01-14 | 2012-07-19 | California Institute Of Technology | Nanotextured surfaces and related methods, systems, and uses |
| RU2498883C1 (en) * | 2012-06-19 | 2013-11-20 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" | Method of making compressor blade |
-
2016
- 2016-12-21 EA EA201700153A patent/EA032992B1/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| EA032992B1 (en) | 2019-08-30 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MM4A | Lapse of a eurasian patent due to non-payment of renewal fees within the time limit in the following designated state(s) |
Designated state(s): AM AZ BY KZ KG TJ TM RU |