CS229905B2 - Gas turbine blade protected with ceramic deposit - Google Patents
Gas turbine blade protected with ceramic deposit Download PDFInfo
- Publication number
- CS229905B2 CS229905B2 CS732077A CS732077A CS229905B2 CS 229905 B2 CS229905 B2 CS 229905B2 CS 732077 A CS732077 A CS 732077A CS 732077 A CS732077 A CS 732077A CS 229905 B2 CS229905 B2 CS 229905B2
- Authority
- CS
- Czechoslovakia
- Prior art keywords
- turbine blade
- gas turbine
- blade
- ceramic deposit
- protected
- Prior art date
Links
- 239000000919 ceramic Substances 0.000 title description 4
- 239000002184 metal Substances 0.000 claims description 7
- 238000005524 ceramic coating Methods 0.000 claims description 6
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 6
- 239000003546 flue gas Substances 0.000 description 6
- 238000001816 cooling Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 230000001151 other effect Effects 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Description
(54) Lopatka plynovej turbíny, chráněná keramickým nánosom(54) Gas turbine blade protected by ceramic coating
Vynález sa týká leteckých turbínových lopatiek, v ktorých sa rieši ochrana lopatky keramickým nánosom po obidvoch stranách nosné) kovověj časti lopatky.The invention relates to aircraft turbine blades in which the protection of the blade by ceramic coating on both sides of the support metal part of the blade is provided.
Doteraz známe turbínové lopatky leteckých motorov, tepelných agregátov a automobilových pokusných turbín sú priamo vystavené tepelným účinkom o 650 až 900 °C a opotřebením lopatky spalinami.The prior art turbine blades of aircraft engines, heat units and automotive test turbines are directly exposed to thermal effects of 650 to 900 ° C and to blade wear by flue gas.
Vysoká teplota spalin zníži pevnost exponovaných častí lopatky. Preto, pre vysokú teplotu spalin, ktorá je žiadúca pre zvýšenie termodynamickej účinnosti, turbínové lopatky nemožu spořahlivo pracovat nad 900 °C.High flue gas temperature will reduce the strength of exposed blade parts. Therefore, due to the high flue gas temperature, which is desirable to increase thermodynamic efficiency, the turbine blades cannot reliably operate above 900 ° C.
Hoře uvedené nedostatky sú odstránené použitím keramického nánosu podta vynálezu, jej podstatou je také zhotovenie turbínovej lopatky, kde po obidvoch stranách na nosnú kovovú časť lopatky je připevněná súvislá keramická vrstva. Nosná kovová časť je opatřená rebrami a otvormi, zabezpečujúcimi držanie povrchového keramického nánosu, ktorý obaluje časť lopatky vystavená priamym účinkom výtokových plynov.The above-mentioned drawbacks are eliminated by the use of a ceramic deposit according to the invention, the essence of which is the construction of a turbine blade wherein a continuous ceramic layer is attached to both sides of the blade support metal part. The supporting metal part is provided with ribs and openings to hold the surface ceramic coating that surrounds the blade portion exposed to the direct effects of the effluent gases.
Použitím keramického nánosu u turbínových lopatiek je možné zvýšit teplotu spalin z 900 °C až na 1300 °C. Keramický nános vytvára izolačnú vrstvu, ktorá chrání nosnú kovovú časť před tepelným a iným účinkom spalin.By using a ceramic coating on turbine blades, the flue gas temperature can be increased from 900 ° C to 1300 ° C. The ceramic coating forms an insulating layer which protects the supporting metal part from the thermal and other effects of the flue gas.
Zvýšením teploty spalin sa zvýši vnútorná termodynamická účinnost o 8 %. Chladenie sa prevádza sáláním tepla do chladiaceho registra. Tým sa dosiahne účinnejšie chladenie a rovnoměrné rozloženie tepelného póla.Increasing the flue gas temperature increases the internal thermodynamic efficiency by 8%. Cooling is performed by radiating heat to the cooling register. This results in a more efficient cooling and uniform distribution of the heat pole.
Riešenie turbínové) lopatky je na priloženom obrázku, kde na obr. 1 je celkový pohřad na lopatku s čiarkovane vyznačenými úpravami. Na obr. 2 je znázorněná turbinová lopatka s rebrami a otvormi v řeze A—B, a na. obr. 3 je znázorněný profil lopatky v řeze C—D.The solution of the turbine blade is shown in the attached figure, where in FIG. 1 is a general scoop with dotted lines. In FIG. 2 shows a turbine blade with ribs and openings in section A-B, and on. Fig. 3 shows a sectional view of the blade in section C-D.
Na nosnej kovověj časti turbínovej lopatky 1 sú umiestnené otvory 2, a kovové rebrá 3, zabezpečujúcimi držanie povrchového súvislého keramického nánosu 4.On the supporting metal part of the turbine blade 1 are apertures 2, and metal ribs 3, ensuring the holding of the surface continuous ceramic deposit 4.
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CS732077A CS229905B2 (en) | 1977-11-09 | 1977-11-09 | Gas turbine blade protected with ceramic deposit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CS732077A CS229905B2 (en) | 1977-11-09 | 1977-11-09 | Gas turbine blade protected with ceramic deposit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CS229905B2 true CS229905B2 (en) | 1984-07-16 |
Family
ID=5422115
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CS732077A CS229905B2 (en) | 1977-11-09 | 1977-11-09 | Gas turbine blade protected with ceramic deposit |
Country Status (1)
| Country | Link |
|---|---|
| CS (1) | CS229905B2 (en) |
-
1977
- 1977-11-09 CS CS732077A patent/CS229905B2/en unknown
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