JP5566755B2 - タービンエンジン用の動翼 - Google Patents
タービンエンジン用の動翼 Download PDFInfo
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- JP5566755B2 JP5566755B2 JP2010092706A JP2010092706A JP5566755B2 JP 5566755 B2 JP5566755 B2 JP 5566755B2 JP 2010092706 A JP2010092706 A JP 2010092706A JP 2010092706 A JP2010092706 A JP 2010092706A JP 5566755 B2 JP5566755 B2 JP 5566755B2
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- Prior art keywords
- trailing edge
- tip
- trench
- blade
- blade tip
- 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.)
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- 238000001816 cooling Methods 0.000 claims description 44
- 230000007423 decrease Effects 0.000 claims description 3
- 239000003507 refrigerant Substances 0.000 description 11
- 238000000576 coating method Methods 0.000 description 7
- 239000000567 combustion gas Substances 0.000 description 7
- 238000013461 design Methods 0.000 description 7
- 239000007789 gas Substances 0.000 description 7
- 239000011248 coating agent Substances 0.000 description 6
- 239000002826 coolant Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 229910000951 Aluminide Inorganic materials 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 230000003647 oxidation Effects 0.000 description 3
- 238000007254 oxidation reaction Methods 0.000 description 3
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 239000003963 antioxidant agent Substances 0.000 description 1
- 230000003078 antioxidant effect Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000012552 review Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
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
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
12 ガス
14 軸方向の中心軸線
16 ロータディスク
18 動翼
20 タービンシュラウド
22 ダブテール
24 中空のエーロフォイル
26 プラットフォーム
28 正圧側側壁
30 負圧側側壁
32 前縁
34 後縁
36 内側翼根部
38 動翼端
44 膜冷却孔
46 後縁の放出孔
48 翼端プレート
50 正圧側翼端壁
52 負圧側翼端壁
60 翼端中間翼弦線
62 スクイーラ翼端キャビティ
70 動翼
72 後縁トレンチ
74 トレンチ冷却孔
80 動翼
85 動翼
90 動翼
Claims (8)
- ガスタービンエンジン用のタービン動翼(18)の動翼端(38)であって、前記タービン動翼(18)が、エーロフォイル(24)、および前記エーロフォイル(24)をタービンシュラウド(20)の内側で半径方向の軸線に沿ってロータディスク(16)に取り付けるための翼根部(36)と、前記翼根部(36)から動翼端(38)へ延び、前縁(32)および後縁(34)において互いに結合する正圧側側壁(28)および負圧側側壁(30)と、動翼端(38)に形成されるスクイーラ翼端キャビティ(62)とを含んでおり、動翼端(38)が、
前記スクイーラ翼端キャビティ(62)の後端から始まり、概して動翼端(38)の前記後縁(34)に向かって延びる後縁トレンチ(72)と、
前記正圧側側壁(28)の半径方向外側の縁部と前記負圧側側壁(30)の半径方向外側の縁部との間に延びる翼端プレート(48)と
を備えていて、
前記スクイーラ翼端キャビティ(62)が、前記翼端プレート(48)から半径方向外側へ延び前記前縁(32)から前記後縁(34)まで横断する正圧側翼端壁(50)によって第1の側部に形成されていて、正圧側翼端壁(50)が前記正圧側側壁(28)の終端にほぼ隣接して存在しているとともに、前記翼端プレート(48)から半径方向外側へ延び前記前縁(32)から前記後縁(34)まで横断する負圧側翼端壁(52)によって第2の側部に形成されていて、負圧側翼端壁(52)が前記負圧側側壁(30)の終端にほぼ隣接して存在しており、
前記後縁トレンチ(72)が、前記スクイーラ翼端キャビティ(62)から前記動翼端(38)の前記後縁(34)の前方のある位置まで延びる第1の後縁トレンチ(72)を含んでいて、前記第1の後縁トレンチ(72)の下流の終端点の下流に、第2の後縁トレンチ(72)が形成されている、動翼端(38)。 - 翼端中間翼弦線(60)が、前記正圧側翼端壁(50)と前記負圧側翼端壁(52)の間のほぼ中点を結んでいる、前記前縁(32)から前記後縁(34)まで延びる基準線を含み、
前記後縁トレンチ(72)が、前記翼端中間翼弦線(60)とほぼ位置合わせされる、請求項1記載の動翼端(38)。 - 前記後縁トレンチ(72)の経路の形が、直線形、弓形、サーペンタイン形およびジグザグ形の1つであり、
前記後縁トレンチ(72)の輪郭が、半楕円形、長方形、半円形、三角形、台形、「V」字形および「U」字形の1つである、請求項1又は請求項2記載の動翼端(38)。 - 前記後縁トレンチ(72)の深さが、それが前記スクイーラ翼端キャビティ(62)から前記動翼端(38)の前記後縁(34)に向かって延びるとき、実質的に一定であり、
前記後縁トレンチ(72)の前記深さが、前記スクイーラ翼端キャビティ(62)の前記後端の深さの100%〜75%の深さを有する、請求項1乃至請求項3のいずれか1項記載の動翼端(38)。 - 前記後縁トレンチ(72)の深さが、前記トレンチ(72)が前記動翼端(38)の前記後縁(34)に向かって延びるにつれて徐々に浅くなり、
前記後縁トレンチ(72)の前端における前記深さが、前記スクイーラ翼端キャビティ(62)の前記後端の深さの100%〜75%の深さを有し、前記後縁トレンチ(72)の後端における前記深さが、前記スクイーラ翼端キャビティ(62)の前記後端の深さの50%〜10%の深さを有する、請求項1記載の動翼端(38)。 - 前記後縁トレンチ(72)が、前記スクイーラ翼端キャビティ(62)から前記動翼端(38)の前記後縁(34)に向かって延びるとき、実質的に一定の幅を有し、
前記後縁トレンチ(72)の前記幅が、前記スクイーラ翼端キャビティ(62)の前記後端の幅の80%〜40%の幅を有する、請求項1記載の動翼端(38)。 - 前記後縁トレンチ(72)の幅が、前記動翼端(38)の前記後端の形が狭くなるのに比例して狭くなり、
前記後縁トレンチ(72)の幅が、前記動翼端(38)の幅の30%〜70%の幅を有する、請求項1記載の動翼端(38)。 - 前記後縁トレンチ(72)が少なくとも1つのトレンチ冷却孔(74)を含み、前記トレンチ冷却孔(74)が、前記エーロフォイル(24)内の1つまたは複数の冷却キャビティに接続する前記後縁トレンチ(72)内の開口部を含む、請求項1乃至請求項7のいずれか1項記載の動翼端(38)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/425,434 | 2009-04-17 | ||
US12/425,434 US8157504B2 (en) | 2009-04-17 | 2009-04-17 | Rotor blades for turbine engines |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2010249138A JP2010249138A (ja) | 2010-11-04 |
JP5566755B2 true JP5566755B2 (ja) | 2014-08-06 |
Family
ID=42125920
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2010092706A Active JP5566755B2 (ja) | 2009-04-17 | 2010-04-14 | タービンエンジン用の動翼 |
Country Status (4)
Country | Link |
---|---|
US (1) | US8157504B2 (ja) |
EP (1) | EP2243930B1 (ja) |
JP (1) | JP5566755B2 (ja) |
CN (2) | CN105065064A (ja) |
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US20140044557A1 (en) * | 2012-08-09 | 2014-02-13 | General Electric Company | Turbine blade and method for cooling the turbine blade |
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2009
- 2009-04-17 US US12/425,434 patent/US8157504B2/en active Active
-
2010
- 2010-04-14 EP EP10159927.2A patent/EP2243930B1/en active Active
- 2010-04-14 JP JP2010092706A patent/JP5566755B2/ja active Active
- 2010-04-16 CN CN201510429392.8A patent/CN105065064A/zh active Pending
- 2010-04-16 CN CN2010101678343A patent/CN101943028A/zh active Pending
Also Published As
Publication number | Publication date |
---|---|
EP2243930A2 (en) | 2010-10-27 |
US8157504B2 (en) | 2012-04-17 |
EP2243930A3 (en) | 2012-01-04 |
EP2243930B1 (en) | 2016-03-30 |
US20100266410A1 (en) | 2010-10-21 |
CN101943028A (zh) | 2011-01-12 |
CN105065064A (zh) | 2015-11-18 |
JP2010249138A (ja) | 2010-11-04 |
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