EP3307989A1 - Gasturbinenschaufel oder verdichterschaufel mit anti-fretting-beschichtung im schaufelfussbereich und rotor - Google Patents
Gasturbinenschaufel oder verdichterschaufel mit anti-fretting-beschichtung im schaufelfussbereich und rotorInfo
- Publication number
- EP3307989A1 EP3307989A1 EP15751016.5A EP15751016A EP3307989A1 EP 3307989 A1 EP3307989 A1 EP 3307989A1 EP 15751016 A EP15751016 A EP 15751016A EP 3307989 A1 EP3307989 A1 EP 3307989A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- rotor
- polymer coating
- compressor
- region
- 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.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/34—Blade mountings
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
Definitions
- the invention relates to a gas turbine blade or a
- Compressor blade which has a polymer coating in the fastening ⁇ tion area and a rotor.
- a blade is positively connected in the groove area or attachment area with a wheel disc via a corresponding groove.
- the assembly and disassembly of the blades takes place in the axial groove direction.
- Blades are loaded during operation both by the centrifugal force as a function of blade weight and the rotor speed and by the aerodynamic forces. These forces must be taken in the contact area between the blade root and Radin-groove, the so-called. Tragflanken Scheme on ⁇ .
- Coatings used to reduce or prevent "fretting" findings are metallic, eg CuNiln or NiTiCr, for example cold spray spraying, flame spraying and plasma spraying, such as HVOF "High Velocity Oxygen Fuel Spray” or "High Velocity Oxygen Fuel Spray” APS.
- a disadvantage of the coatings used so far is that the components of the coating as well as the material of the wheel disc are metallic. Thus, similar materials are in contact, which promotes adhesion / cold welding. Sequence ⁇ Lich problems can occur at the assembly / disassembly despite CuNiln coating in the contact region. Moreover, damage to the previously applied coatings can only be repaired with great effort.
- Compressor blade according to claim 1 and a rotor according to ⁇ demanding. 5
- Figure 1 is a plan view of a built-turbine or
- FIG. 2 shows a three-dimensional representation of a Turbi ⁇ denominator or compressor blade.
- FIG. 1 shows a part of a rotor 1 which has a wheel disc 4 with a groove area 13 inside the wheel disc 4, in which 13 a turbine blade 6 or a turbine blade 6
- Compressor blade 6 is arranged. From the blade 6, a blade root 7 is inserted in the groove region 13.
- An airfoil 10 of the blade 6 protrudes beyond an outer surface 29 of the wheel disc 4.
- the blade root 7 Seen in the longitudinal direction 11 of the blade 6, the blade root 7 has a lower region 20, which is slightly convexly curved .
- a more curved portion 23 which is also curved convex.
- a support edge region 24 connects, which comes into contact with the wheel disc 4.
- the supporting flank area 24 is flat.
- the support flank region 24 is adjoined optionally by a further end region 26, which can be embodied differently and here runs perpendicular to the surface 29 of the wheel disc 4.
- the support flank region 24, in particular the entire blade root 20, 23, 24, 26, in particular without the end face 30 of the blade root 7, in particular of the compressor blade, is provided with a polymer coating 25.
- the polymer coating 25 then preferably extends over the entire axial length of the blade root 7.
- an inner surface 22 of the groove region 13 may have a polymer coating, ie the wheel disc 4. This polymer coating may be present in addition to the polymer coating 25 of the blade 6 or alternatively. It then also preferably extends over the entire axial length of the groove region 13.
- This coating is preferably based on one or more ⁇ ren fluoropolymers, such as polytetrafluoroethylene (PTFE),
- PTFE polytetrafluoroethylene
- PFA Perfluoroalkoxy
- FEP perfluoroethylene-propylene
- Polymer coating 25 of the blade 6 or the groove portion 13 are embedded.
- these coating systems can reduce the energy input by relative movement between the components blade and wheel disc groove and reduce or prevent possible “fretting” and thus also “fretting fatigue”.
- Polymer-based coating 25 is the use temperature. This allows for compressors, depending on the
- Supporting flank area 24 are uncoated:
- Compressor blade 6 shown in three dimensions.
- the support flank region 24 comes to be damaged, in particular only this region is coated with a polymer 25.
- the polymer coating 25 preferably extends over the entire axial length of the support flank region 24 and may also include the entire foot region 20, 23, 24, 26.
- the polymer coating 25 for the blade root 7 or the groove region 13 may be fluoropolymer-based and may also contain in particular one or more solid lubricants.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PL15751016T PL3307989T3 (pl) | 2015-08-19 | 2015-08-19 | Łopatka turbiny gazowej albo łopatka sprężarki z powłoką anty-frettingową w obszarze podstawy łopatki i wirnik |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/EP2015/069013 WO2017028912A1 (de) | 2015-08-19 | 2015-08-19 | Gasturbinenschaufel oder verdichterschaufel mit anti-fretting-beschichtung im schaufelfussbereich und rotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP3307989A1 true EP3307989A1 (de) | 2018-04-18 |
| EP3307989B1 EP3307989B1 (de) | 2020-09-30 |
Family
ID=53879518
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP15751016.5A Active EP3307989B1 (de) | 2015-08-19 | 2015-08-19 | Gasturbinenschaufel oder verdichterschaufel mit anti-fretting-beschichtung im schaufelfussbereich und rotor |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US11352893B2 (de) |
| EP (1) | EP3307989B1 (de) |
| KR (1) | KR102045389B1 (de) |
| CN (1) | CN107923251B (de) |
| PL (1) | PL3307989T3 (de) |
| WO (1) | WO2017028912A1 (de) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU2019253039A1 (en) * | 2018-04-12 | 2020-12-03 | Resource West, Inc. | Impeller for ambient water evaporators, and related system and method |
| DE102020212752A1 (de) | 2020-10-08 | 2022-04-14 | MTU Aero Engines AG | Verfahren zum Herstellen eines Rotors für eine Strömungsmaschine, Rotor für eine Strömungsmaschine und Strömungsmaschine mit einem Rotor |
Family Cites Families (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3133158C1 (de) * | 1981-08-21 | 1982-12-16 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Pressflaechen-Zwischenlage aus Metall und Verfahren zur Herstellung derselben |
| US4790723A (en) * | 1987-01-12 | 1988-12-13 | Westinghouse Electric Corp. | Process for securing a turbine blade |
| US4820126A (en) * | 1988-02-22 | 1989-04-11 | Westinghouse Electric Corp. | Turbomachine rotor assembly having reduced stress concentrations |
| US5087174A (en) * | 1990-01-22 | 1992-02-11 | Westinghouse Electric Corp. | Temperature activated expanding mineral shim |
| US5160243A (en) * | 1991-01-15 | 1992-11-03 | General Electric Company | Turbine blade wear protection system with multilayer shim |
| US5356545A (en) * | 1991-01-15 | 1994-10-18 | General Electric Company | Curable dry film lubricant for titanium alloys |
| US5179153A (en) * | 1991-09-09 | 1993-01-12 | E. I. Du Pont De Nemours And Company | Wear resistant polyimide composition |
| US5573377A (en) * | 1995-04-21 | 1996-11-12 | General Electric Company | Assembly of a composite blade root and a rotor |
| US6102664A (en) * | 1995-12-14 | 2000-08-15 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Blading system and method for controlling structural vibrations |
| US6290466B1 (en) * | 1999-09-17 | 2001-09-18 | General Electric Company | Composite blade root attachment |
| FR2918703B1 (fr) * | 2007-07-13 | 2009-10-16 | Snecma Sa | Ensemble de rotor de turbomachine |
| GB2452515B (en) * | 2007-09-06 | 2009-08-05 | Siemens Ag | Seal coating between rotor blade and rotor disk slot in gas turbine engine |
| FR2934873B1 (fr) * | 2008-08-06 | 2011-07-08 | Snecma | Dispositif amortisseur de vibrations pour attaches d'aubes. |
| GB0911459D0 (en) | 2009-07-02 | 2009-08-12 | Rolls Royce Plc | An assembly providing contaminant removal |
| US20110142678A1 (en) * | 2010-11-23 | 2011-06-16 | General Electric Company | Erosion protection coating for rotor blade of wind turbine |
| GB201106278D0 (en) * | 2011-04-14 | 2011-05-25 | Rolls Royce Plc | Annulus filler system |
| BR112015028251A2 (pt) * | 2013-05-29 | 2017-07-25 | Gen Electric | aerofólio compósito |
-
2015
- 2015-08-19 CN CN201580082510.0A patent/CN107923251B/zh active Active
- 2015-08-19 WO PCT/EP2015/069013 patent/WO2017028912A1/de not_active Ceased
- 2015-08-19 PL PL15751016T patent/PL3307989T3/pl unknown
- 2015-08-19 US US15/752,895 patent/US11352893B2/en active Active
- 2015-08-19 EP EP15751016.5A patent/EP3307989B1/de active Active
- 2015-08-19 KR KR1020187007308A patent/KR102045389B1/ko active Active
Also Published As
| Publication number | Publication date |
|---|---|
| PL3307989T3 (pl) | 2021-03-08 |
| WO2017028912A1 (de) | 2017-02-23 |
| KR20180041172A (ko) | 2018-04-23 |
| CN107923251B (zh) | 2020-09-08 |
| US11352893B2 (en) | 2022-06-07 |
| US20180245475A1 (en) | 2018-08-30 |
| CN107923251A (zh) | 2018-04-17 |
| KR102045389B1 (ko) | 2019-11-15 |
| EP3307989B1 (de) | 2020-09-30 |
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