JP2015520322A - ガスタービンエンジンの壁 - Google Patents
ガスタービンエンジンの壁 Download PDFInfo
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- JP2015520322A JP2015520322A JP2015517420A JP2015517420A JP2015520322A JP 2015520322 A JP2015520322 A JP 2015520322A JP 2015517420 A JP2015517420 A JP 2015517420A JP 2015517420 A JP2015517420 A JP 2015517420A JP 2015520322 A JP2015520322 A JP 2015520322A
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- 238000001816 cooling Methods 0.000 claims abstract description 73
- 230000007423 decrease Effects 0.000 claims description 6
- 239000000567 combustion gas Substances 0.000 description 12
- 238000009792 diffusion process Methods 0.000 description 12
- 239000007789 gas Substances 0.000 description 9
- 101150014330 dfa2 gene Proteins 0.000 description 6
- 238000000926 separation method Methods 0.000 description 5
- 238000007664 blowing Methods 0.000 description 3
- 230000006870 function Effects 0.000 description 3
- 230000006872 improvement Effects 0.000 description 3
- 239000000112 cooling gas Substances 0.000 description 2
- 101150061638 dfa3 gene Proteins 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000001143 conditioned effect Effects 0.000 description 1
- UFULAYFCSOUIOV-UHFFFAOYSA-N cysteamine Chemical compound NCCS UFULAYFCSOUIOV-UHFFFAOYSA-N 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
-
- 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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- 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
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
-
- 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
- F05D2240/11—Shroud seal segments
-
- 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
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
-
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03042—Film cooled combustion chamber walls or domes
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
12 中心軸
14 ファン
16 (軸流)圧縮機
18 燃焼器
19 高圧タービン
20 タービンノズル
22 タービン
23 タービンノズルバンド/外側ノズルバンド
24 低圧タービン
25 (タービン)ロータ翼
26 排気部ライナ
27 タービンシュラウド
28 空気
29 外側ライナ
30 燃焼ガス/冷却ガス
31 羽根
32 壁
34 内壁面/内面
36 外面/外側面/外壁面
37 列
38 (フィルム)冷却孔
40 入口(端)
42 出口
44 入口穴
46 出口(端)
48 チャネル
49 第1のチャネル
50 尾根
51 第2のチャネル
52 底
53 軸
54 側壁
55 横断軸
60 (マキシモ)冷却孔
62 チャネル
64 底
66 側壁
68 側壁
70 外縁
72 後縁
80 冷却孔/ブーメラン孔
A 傾斜角度
B 傾斜角度/レイバック角度/排出角度
C 傾斜角度
DFA 角度
DFA2 角度
DFA3 角度
E 横幅
G 距離
H 全高
H2 高さ
I 角度
J フープ方向
M 吹き出し比
Y 横幅
Claims (15)
- 少なくとも1つのフィルム冷却孔(38)が定められた内面(34)および反対側の外面(36)
を備え、
前記少なくとも1つのフィルム冷却孔(38)は、前記内面(34)から延びる斜めの入口穴(44)と、該斜めの入口穴(44)の出口端(46)から横方向に分岐する1対のチャネル(48)とを備え、
前記1対のチャネル(48)は、実質的に一定の幅を有し、ブーメラン型の断面形状を形成するように尾根(50)によって隔てられているガスタービンエンジンの壁(32)。 - 前記1対のチャネル(48)のうちの少なくとも一方が、実質的に丸みを帯びた断面形状を有する底を備える請求項1に記載の壁(32)。
- 前記1対のチャネル(48)のうちの少なくとも一方が、前記斜めの入口穴(44)の直径と実質的に同様の幅を有する請求項1又は2に記載の壁(32)。
- 前記尾根(50)の深さが、該尾根(50)が前記外面(36)に向かって延びるにつれて実質的に一定の傾斜にて減少している請求項1乃至3のいずれか1項に記載の壁(32)。
- 前記尾根(50)が、前記1対のチャネル(48)の底に定められる縁を備え、該縁が、前記斜めの入口穴(44)の出口端(46)から或る距離だけ離されている請求項1乃至4のいずれか1項に記載の壁(32)。
- 前記尾根(50)が、実質的に一定の幅を備える請求項1乃至5のいずれか1項に記載の壁(32)。
- 前記1対のチャネル(48)の深さが、前記斜めの入口穴(44)の出口端(46)から前記外面(36)に向かって実質的に一定の傾斜にて減少している請求項1乃至6のいずれか1項に記載の壁(32)。
- 前記1対のチャネル(48)が、前記尾根(50)の傾斜角度よりも浅い傾斜角度を有する請求項1乃至7のいずれか1項に記載の壁(32)。
- 少なくとも1つのフィルム冷却孔(38)が定められた内面(34)および反対側の外面(36)
を備え、
前記少なくとも1つのフィルム冷却孔(38)は、前記内面(34)から延びる斜めの入口穴(44)と、該斜めの入口穴(44)の出口端(46)から横方向に分岐する1対のチャネル(48)とを備え、
前記1対のチャネル(48)は、実質的に平坦な底を有し、ブーメラン型の断面形状を形成するように尾根(50)によって隔てられているガスタービンエンジンの壁(32)。 - 前記実質的に平坦な底の幅が、前記斜めの入口穴(44)の出口端(46)から前記1対のチャネル(48)の後縁に向かって分岐している請求項9に記載の壁(32)。
- 前記尾根(50)の深さが、該尾根(50)が前記外面(36)に向かって延びるにつれて大きくなる傾斜にて減少している請求項9又は10に記載の壁(32)。
- 前記1対のチャネル(48)が、前記実質的に平坦な底から前記外面(36)に延びる少なくとも1つの側壁を備える請求項9乃至11のいずれか1項に記載の壁(32)。
- 前記少なくとも1つの側壁が、前記実質的に平坦な底の両方の縁から延びる1対の側壁を含み、該1対の側壁が、前記実質的に平坦な底から前記外面(36)に向かって分岐している請求項12に記載の壁(32)。
- 前記1対のチャネル(48)が、約20°〜約100°の間の角度で分岐している請求項9乃至13のいずれか1項に記載の壁(32)。
- 前記1対のチャネル(48)が、前記斜めの入口穴(44)から排出される空気の流れを分割して拡散させるように構成されている請求項9乃至14のいずれか1項に記載の壁(32)。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201261659083P | 2012-06-13 | 2012-06-13 | |
US61/659,083 | 2012-06-13 | ||
PCT/US2013/045619 WO2013188645A2 (en) | 2012-06-13 | 2013-06-13 | Gas turbine engine wall |
Publications (1)
Publication Number | Publication Date |
---|---|
JP2015520322A true JP2015520322A (ja) | 2015-07-16 |
Family
ID=48747724
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2015517420A Pending JP2015520322A (ja) | 2012-06-13 | 2013-06-13 | ガスタービンエンジンの壁 |
Country Status (7)
Country | Link |
---|---|
US (1) | US10386069B2 (ja) |
EP (1) | EP2861909A2 (ja) |
JP (1) | JP2015520322A (ja) |
CN (1) | CN104364581B (ja) |
BR (1) | BR112014031176A2 (ja) |
CA (1) | CA2875028A1 (ja) |
WO (1) | WO2013188645A2 (ja) |
Cited By (1)
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JP2020531746A (ja) * | 2017-08-30 | 2020-11-05 | シーメンス アクティエンゲゼルシャフト | 高温ガス構成要素の壁、および壁を備える高温ガス構成要素 |
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US11313235B2 (en) * | 2015-03-17 | 2022-04-26 | General Electric Company | Engine component with film hole |
US10030525B2 (en) * | 2015-03-18 | 2018-07-24 | General Electric Company | Turbine engine component with diffuser holes |
US10208602B2 (en) * | 2015-04-27 | 2019-02-19 | United Technologies Corporation | Asymmetric diffuser opening for film cooling holes |
CA2933884A1 (en) * | 2015-06-30 | 2016-12-30 | Rolls-Royce Corporation | Combustor tile |
US10392947B2 (en) | 2015-07-13 | 2019-08-27 | General Electric Company | Compositions and methods of attachment of thick environmental barrier coatings on CMC components |
US10168051B2 (en) | 2015-09-02 | 2019-01-01 | General Electric Company | Combustor assembly for a turbine engine |
US9976746B2 (en) | 2015-09-02 | 2018-05-22 | General Electric Company | Combustor assembly for a turbine engine |
US10197278B2 (en) | 2015-09-02 | 2019-02-05 | General Electric Company | Combustor assembly for a turbine engine |
US11149646B2 (en) | 2015-09-02 | 2021-10-19 | General Electric Company | Piston ring assembly for a turbine engine |
US10563867B2 (en) | 2015-09-30 | 2020-02-18 | General Electric Company | CMC articles having small complex features for advanced film cooling |
US20180135520A1 (en) * | 2016-11-16 | 2018-05-17 | United Technologies Corporation | Large area ratio cooling holes |
CN107725115B (zh) * | 2017-04-28 | 2019-07-30 | 中国航发湖南动力机械研究所 | 航空发动机热端部件的翼型气膜孔及电极 |
US11402097B2 (en) | 2018-01-03 | 2022-08-02 | General Electric Company | Combustor assembly for a turbine engine |
RU197365U1 (ru) * | 2020-02-04 | 2020-04-23 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Рыбинский государственный авиационный технический университет имени П.А. Соловьева" | Элемент газовой турбины с пленочным охлаждением |
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- 2013-06-13 JP JP2015517420A patent/JP2015520322A/ja active Pending
- 2013-06-13 WO PCT/US2013/045619 patent/WO2013188645A2/en active Application Filing
- 2013-06-13 CN CN201380031113.1A patent/CN104364581B/zh active Active
- 2013-06-13 BR BR112014031176A patent/BR112014031176A2/pt not_active IP Right Cessation
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JP2020531746A (ja) * | 2017-08-30 | 2020-11-05 | シーメンス アクティエンゲゼルシャフト | 高温ガス構成要素の壁、および壁を備える高温ガス構成要素 |
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Also Published As
Publication number | Publication date |
---|---|
BR112014031176A2 (pt) | 2017-06-27 |
CA2875028A1 (en) | 2013-12-19 |
WO2013188645A2 (en) | 2013-12-19 |
CN104364581A (zh) | 2015-02-18 |
CN104364581B (zh) | 2016-05-18 |
WO2013188645A3 (en) | 2014-02-27 |
EP2861909A2 (en) | 2015-04-22 |
US10386069B2 (en) | 2019-08-20 |
US20150159871A1 (en) | 2015-06-11 |
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