JPS5867904A - Cooling type power wing of gas turbine engine - Google Patents
Cooling type power wing of gas turbine engineInfo
- Publication number
- JPS5867904A JPS5867904A JP13106882A JP13106882A JPS5867904A JP S5867904 A JPS5867904 A JP S5867904A JP 13106882 A JP13106882 A JP 13106882A JP 13106882 A JP13106882 A JP 13106882A JP S5867904 A JPS5867904 A JP S5867904A
- Authority
- JP
- Japan
- Prior art keywords
- rotor blade
- perforated
- hollow
- plate
- cooling
- 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.)
- Pending
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
- F01D5/12—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
- F01D5/187—Convection cooling
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】
本発明はガスタービン・エンジンの冷−ｋｇ代仙だに関
する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a cold-kg engine for a gas turbine engine.
ガスタービン・エンパンンの勧鴫はｆ”ｌう力為の１杉
氏の翼の冷却を必要とするような高い温度で作動するこ
とがしばしは要求される。翼の冷却に＃に！Ｉ！利な方
法の一つけ楓の中の通路に冷却空気金流すことを含む。Gas turbine engines are often required to operate at such high temperatures that they require cooling of the blades. An advantageous method involves flowing cooling air through the passages within the maple.
冷却空気は都合のよい任意な空気源から収ることがでへ
るが、４常はカスタービン・エンパ２ンの田縮慨の高圧
段から抽出される。冷却空気社数多（のＵなる通路のう
ち所安の冷却バタ−ンにより決まる任はの一つに沿って
翼の中を流−れることかできる。もしも翼の翼杉部の成
る部分が局ｇ区的な過熱を受けやすい場合は、いわゆる
「衝突冷却」によりこれらの部分を冷却することができ
る。衝突冷却の技法は中空翼の内面の冷却を必要とする
部分に冷却空気の噴流を振向けることを含んでいる。Cooling air can come from any convenient air source, but is often extracted from the high pressure stage of the cast turbine engine 2 tank. Cooling air can flow through the wing along one of the many channels (U), the role of which is determined by the cooling pattern at the location. If areas are susceptible to localized overheating, these areas can be cooled by so-called "impingement cooling".The impingement cooling technique involves directing jets of cooling air to the areas of the inner surface of the hollow wing that require cooling. It includes directing.
そのような冷却空気の噴流を得る方法は幾つか有る。一
つの方法はたとえば鋳造などにより中空ｇを形成させ、
冷却空気を流す通路から冷却すべ缶部分を隔離する、翼
と一体の穴明缶壁を設けることである。通路からの冷却
空気は穴明缶壁を通って、冷却すべ点部分に衝突する冷
却空気噴流と−なる。このような配冒の欠点Ｕ、＠と一
体の穴明き壁が他の翼の部分に比較して冷却され過ぎる
傾向があり、従って熱６カのために金製を生じ易い。There are several ways to obtain such a jet of cooling air. One method is to form a hollow g by, for example, casting,
A perforated can wall integral with the blade is provided to isolate the cooling can part from the passage through which cooling air flows. Cooling air from the passage passes through the perforated can wall and forms a jet of cooling air that impinges on the cooling points. The disadvantage of such a distribution is that the perforated wall integral with the wing tends to be too cooled compared to other parts of the wing and is therefore susceptible to heat build-up.
冷却空気噴流を得るもう一つの方法は中空翼の中にイン
を一トを設けることである。このインプートは中に空気
を供給するチューブの、形式をしており、冷却すべ微減
の部分に冷却空気を振向けるための小さな穴が数多（明
い
ＩＯをもたらすこと、チューブを輯の中にうま（止める
ことが困ｄＴあること、またインサートラ入れるために
痙形部分の空力的外形を悪（する可能性のあることなど
から、インサートはあ１り好ｌし、（ない。Another method of obtaining a cooling air jet is to install an inlet in the hollow wing. This input is in the form of a tube that supplies air inside, with many small holes to direct the cooling air to the area where the cooling surface is slightly reduced. I prefer an insert because it is difficult to stop it, and there is a possibility of changing the aerodynamic shape of the spastic part to accommodate the insert.
効果的な衝突冷却を与え、前記の困難性を事実１峠ける
ことができる、ガスタービン・エンジンの衝突冷却式動
翼を与えることが本発明の一つの目的である。It is an object of the present invention to provide an impingement-cooled rotor blade for a gas turbine engine that provides effective impingement cooling and can in fact overcome one of the above-mentioned difficulties.
タービン・エンジンの冷
部を２つの部分に分割す
るよう処された１枚の穴明缶板を設けられ、その穴明き
板の少（とも過半部分は自由でありまた動翼に付して１
頃糾してａるために、運転中社穴明徴板の少くとも過半
部分が動翼内面に設けられた内方に延びる肋材に密封係
合するように遠心力で押されており、また中空４内部の
一つに冷却空気が供給されるので、冷却Ｔ−Ａが穴明缶
板の穴をｄ過して翼内部のもう一つの部分の内面の少（
とも一部に衝突冷却を与えるようになっている。A perforated can plate is provided which is arranged to divide the cold section of the turbine engine into two parts, the perforated plate having a small portion (the majority of which is free and attached to the rotor blades). 1
During operation, at least a majority portion of the hole marking plate is centrifugally urged into sealing engagement with an inwardly extending rib provided on the inner surface of the rotor blade, and Since cooling air is supplied to one of the interiors of the hollow 4, the cooling T-A passes through the hole d of the perforated can plate and reaches the inner surface of the other part inside the blade.
Both systems are designed to provide some collisional cooling.
は下に添付図面を参照し・）つ１本発明の実施例を説明
する。Embodiments of the invention will now be described with reference to the accompanying drawings.
第１図を参照するに、全体を１０で示された中空勧傭は
、ローター円板（図示せず）の周囲に動翼１Ｕを収付け
るための在来形の翼根部１１と翼杉部１２と痙根部１１
および翼杉部１２をそれぞ７１、Ｉ！！結するプラット
ホーム１６とを含む。Referring to FIG. 1, the hollow blade, indicated as a whole by 10, has a conventional blade root part 11 and a blade part for storing 1U of rotor blades around a rotor disc (not shown). 12 and spastic root 11
and Tsubasagibe 12 respectively 71, I! ! and a platform 16 for connecting.
中Ｑｆｉ’ｌＬ］の内部１４は穴明缶板１７により２つ
の部分１５，１６に分割される。板１７は翼端１８にお
いてのみ、翼杉部１２に暇付けられている。より具体的
には、穴明折板Ｉ７の半径方向外方部分１９は＠翼内部
１５の半径方向外方端に設けられる位置決め部ノＵに係
合するように折曲げられている。穴明Ａ板１７０半径方
向外方部分１ソは、穴明真板１７の残りの部分會励翼１
０に付して自由にしてお（ように１位置決め特性部２０
に溶接される（ろう付けでもよい）。さらに。The interior 14 of the middle Qfi'lL is divided into two parts 15 and 16 by a perforated can plate 17. The plate 17 is attached to the wing section 12 only at the wing tip 18. More specifically, the radially outer portion 19 of the perforated folded plate I7 is bent so as to engage with a positioning portion U provided at the radially outer end of the wing interior 15. The radially outer part 1 of the perforated A plate 170 is the remaining part of the perforated true plate 17.
0 and leave it free (like 1 positioning characteristic part 20
be welded (brazing may also be used). moreover.
穴明な板１７の自由部分は動翼１Ｕに付して１頃斜して
いて、ａｌｌ］ｇｉｏが回転すると、穴明な板１７の自
由部分が泣１６決め部２０の方に遠心力によって曲るよ
うになっている。穴明缶板１７の曲りは動域１０の内面
に設けられて内方に延びる肋材２１により制限される。The free part of the perforated plate 17 is attached to the rotor blade 1U and is inclined at about 1, and when the rotor blade 1U rotates, the free part of the perforated plate 17 is moved toward the determining part 20 by centrifugal force. It is curved. The bending of the perforated can plate 17 is restricted by ribs 21 provided on the inner surface of the moving area 10 and extending inward.
肋材２１け動翼１０の横腹の両側の内面および穴明へ板
１７の半径方向＜ｇ万端の近（に設けられて、肋材２１
が１届同して穴明き仮１７の周囲の・ンールとなる。す
なわち、動ｇ１０の回転ｔこより穴明缶板１７の自由端
が遠心力で押されて＋Ｊカ材２１に密封係合し、それに
より穴２２だけがｌ助虎内１１１］部５）１５．１６の
連通をりえることになる。The ribs 21 are provided in the radial direction of the plate 17 to the inner surface on both sides of the flank of the keeling blade 10 and near the hole in the radial direction of the plate 17.
This will be the area around the hole-opening temporary 17. That is, due to the rotation of the motion g10, the free end of the perforated can plate 17 is pushed by centrifugal force and sealingly engages the +J member 21, so that only the hole 22 is closed. This will result in 16 connections.
Ｗ１ｈｉ１１ｉ！内側部分１ｂＦｉ痩形部分１２の前は
２６に近接しており、 ＋＋ｔｊｒ ！Ｘべ１Ｕの全内
容積の小部分ケ占める。動域内１１４す部分１６は翼形
部分１２の内４の残りを占めており、ざらに４根部１１
の内部を含んでいる。W1hi11i! The front of the inner part 1bFi slim part 12 is close to 26, ++tjr! It occupies a small portion of the total internal volume of 1U of X-beam. The inner motion range 114 portion 16 occupies the remaining 4 of the airfoil portions 12, and roughly the 4 root portions 11
Contains the inside of.
運転中は、動翼１０が敗付けられるガスタービン・エン
・ジンの圧縮機のような都合のよい空気源から勧痙内側
部分１６に冷却空気が供給される。During operation, cooling air is supplied to the convulsive inner section 16 from a convenient air source, such as the compressor of a gas turbine engine on which the rotor blades 10 are defeated.
冷却空気は翼根部１１から動翼内側部分１６に入り、動
翼内側部分１６を画成する楓杉部１２の部分に半径方向
流の対流冷却を与える。異端１８の所で動翼内側部分１
６をふさいでいるキャップ２５に設けられた窓２４全通
して、冷却空気の成る部分が動翼内部１６から排出され
る。しかし冷却空気の残部は板１７の穴゛２２を通過し
て動翼前縁７６の内面に衝突する噴流を杉成し、それに
より前嫌２６に衝突冷却を与える。つぎに冷却空気は動
翼内側部分１５を通過し、穴明き板２７の半径方向外方
の折曲部分１９に設けられた窓２６全通して動翼内９１
１１部分１５から排出されるまで成る程度の対流冷却を
与える。Cooling air enters the rotor blade inner section 16 from the blade root 11 and provides radial flow convective cooling to the portion of the maple section 12 that defines the rotor blade inner section 16 . Inner blade part 1 at heresy 18
A portion of the cooling air is discharged from the inside 16 of the rotor blade through the entire window 24 provided in the cap 25 covering the rotor blade 6 . However, the remainder of the cooling air passes through the holes 22 in the plate 17 and forms a jet that impinges on the inner surface of the blade leading edge 76, thereby providing impingement cooling to the leading edge 76. Next, the cooling air passes through the rotor blade inner portion 15 and passes through the entire window 26 provided in the radially outward bent portion 19 of the perforated plate 27 into the rotor blade 91.
11 until discharged from section 15.
ル端１８にある窓２４．２６を通して冷却空気が＠４内
側部分１ｂ、１６から排出されると述べたけれども、実
際には翼杉部１２の横腹に窓を設けて、そこから排出さ
れる冷１空気が禰形部１２の外面のフィルム冷却を与え
ることもできる。Although it has been mentioned that the cooling air is discharged from the inner part 1b, 16 through the windows 24 and 26 at the end 18 of the wing, in reality, a window is provided in the flank of the wing part 12, and the cooling air is discharged from there. 1 air may also provide film cooling of the outer surface of the ridge 12.
穴明森板１７は遠心力により押されて肋材２１に密封係
合するから、穴明缶板１７と肋材２１との間の冷却空気
の洩れは局限される。それＩＬより本発明は穴明へ仮１
７と肋材２１との間に幼果的なシールが光成することを
保証する。Since the perforated can board 17 is pushed by the centrifugal force into sealing engagement with the ribs 21, leakage of cooling air between the perforated can board 17 and the ribs 21 is localized. From that IL, the present invention is tentatively 1
7 and the ribs 21 to ensure that a seedling seal is formed.
そのうえ、穴明た板１７の過半部分は動Ａ１０に固定的
に取付（丁られていないから、動翼１ｕと穴明な板１７
との間に非常に大きな温窒差が生じても熱応力が生じな
いから問題はない。Moreover, the majority of the perforated plate 17 is fixedly attached to the rotor A10 (since it is not folded, the perforated plate 17 is attached to the rotor blade 1u).
Even if a very large difference in temperature and nitrogen occurs between the two, there is no problem because thermal stress does not occur.
本宅間のもう一つの↑り点は、穴明Ａ板１７と１１ｒ）
材２１との間の摩擦係合により、仮１７が＠痩１０の中
で成る種変の幾動減衰１’ｌＥ用を与える′ことである
。Another ↑ point between the main building is hole A plate 17 and 11r)
Due to the frictional engagement between the material 21 and the material 21, the provisional 17 provides the geometrical damping 1'lE of the material formed within the material 10.
本宅間が動翼のＦｎｌ嫌の衝突冷却に特に限定されるも
のでないことが判る。事実、たとえば楓の１黄１復の部
分に冷却を与えるように、４ｉｕの中の他の立置に穴明
き板１７を設けることができる。もちろん、穴明を板１
７が遠心力によシ押されて翼１０の内面の適当な立１直
におる肋材に密封係合するように穴明Ａ板１７°を楓１
０に灯して傾斜でせなければならないであろう。It can be seen that the method is not particularly limited to Fnl-based impingement cooling of rotor blades. In fact, perforated plates 17 can be provided in other positions within the 4iu, so as to provide cooling to, for example, one yellow part of the maple. Of course, the holes are plate 1.
The hole A plate 17° is inserted into the maple plate 1 so that the plate 7 is pressed by centrifugal force and sealingly engages with the rib at an appropriate vertical position on the inner surface of the wing 10.
You will have to turn it to 0 and tilt it.
また穴明き似１７け必しも翼１０の翼端１８の区域に固
定的に暇付けられる必要はな（、たとえばブラｌトホー
ム１６の区域でｇｉｕに固定的に取付けられることがで
六ることも判る。Also, the perforation 17 need not necessarily be fixedly attached to the wing tip 18 area of the wing 10 (for example, it can be fixedly attached to the GIU in the area of the blast platform 16). I also understand that.
さらに、穴明へ仮を必しもろう付けまたは溶接によりｇ
ｉｕに固定的に収付ける必要はな（、その代りに何ら゛
かの適当な形式の機械的結合により取付けることもでき
る。In addition, the g
It need not be fixedly attached to the iu (but could instead be attached by some suitable type of mechanical connection).
第１図は第２図のＡ−Ａ線に沿う断面で見た。
本宅間による冷却式中空動翼の側面図。
第２図はＩ＠１図のラインＢ−Ｂに沿う断面図。
でおる。
１０・・・＃翼 １７・・・穴明た板２１・・
・肋材
特許出願人 口、−ルス・ロイス拳すミテ・ソド（外２
名）FIG. 1 is a cross-sectional view taken along line A--A in FIG. 2. Side view of Hontakuma's cooled hollow rotor blade. FIG. 2 is a cross-sectional view taken along line BB in FIG. I@1. I'll go. 10...#Wing 17...Perforated plate 21...
・Rib patent application population - Luz Royce Kensmite Sodo (outside 2
given name)
Claims (1)
おいて、該動翼の内部ｔ−２つの部分に分割するような
杉帳を持つ１枚の穴明矢板を設けられ、該穴明矢板の少
（とも過半部分は自由でありまた核動翼［吋して傾斜し
ており、該動翼の内面に内方に延在する肋材を設けられ
ているので、運転中は前記穴明矢板の前記自由部分が前
記肋材に密封係合するように遠心力によって押されてお
り、前記中空動翼内部の前記２つの部分の１つけ運転中
に冷却空気が供給されるので、核冷却空気が前記穴明金
板の穴を禮過して前記動翼内部のもう１つの部分の内面
の少（とも一部に衝突冷却を与えるようにされた。冷却
式中空動翼。 （２）前記穴明き板の小部分が前記動翼の半径方向外方
端区域にて該動翼に固定的に取付けられている。′ｌＩ
！Ｆ許請求の範囲第（１）項に記載の中空動翼。 ＋３） 前記穴明缶板のｔ’４１１記小部分が前記動
画の半径方向外方端区Ｖ！にて４４１勧翼にろう付けさ
れる。 特許請求の範囲第１２１１）ｉＫ記載の中空−翼。 （４）前記穴明Δ板の前記小部分が前記動翼の半径方向
外方端区域にて該動翼にｍ接される。特許請求の範囲第
１２）項に記載の中空動翼。 （５）前記動翼内部の内面の衝突冷却を受ける前記部分
が前記ａ−の前嫌の近（である、￥ｆ許請求の範囲第１
１１項に記載の中空動翼。[Claims] +11 In a cooled hollow rotor blade of a gas turbine engine, a perforated sheet pile is provided with a cedar board that divides the inside of the rotor blade into two parts, and the perforated The majority of the sheet piles are free, and the core rotor blades are inclined at a distance, and the inner surface of the rotor blades is provided with inwardly extending ribs, so that during operation, the said free portion of the perforated sheet pile is pushed by centrifugal force into sealing engagement with said rib, and cooling air is supplied during the one-on operation of said two portions inside said hollow rotor blade; Core cooling air passes through the holes in the perforated metal plate to provide impingement cooling to at least a portion of the inner surface of another portion inside the rotor blade. (Cooled hollow rotor blade.) 2) a small portion of the perforated plate is fixedly attached to the rotor blade in its radially outer end area;
! A hollow rotor blade according to claim (1). +3) The small portion marked t'411 of the perforated can plate is the radially outer end section V of the moving image! It is brazed to the 441 Kan-wing. Claim 1211) Hollow wing according to iK. (4) The small portion of the perforated Δ plate is in contact with the rotor blade in a radially outer end area of the rotor blade. A hollow moving blade according to claim 12). (5) The portion of the inner surface of the rotor blade that receives collision cooling is located near the front end of the a-.
The hollow moving blade according to item 11.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB08129466A GB2106996A (en) | 1981-09-30 | 1981-09-30 | Cooled rotor aerofoil blade for a gas turbine engine |
| GB8129466 | 1981-09-30 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS5867904A true JPS5867904A (en) | 1983-04-22 |
Family
ID=10524826
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP13106882A Pending JPS5867904A (en) | 1981-09-30 | 1982-07-27 | Cooling type power wing of gas turbine engine |
Country Status (4)
| Country | Link |
|---|---|
| JP (1) | JPS5867904A (en) |
| DE (1) | DE3234906A1 (en) |
| FR (1) | FR2513695A1 (en) |
| GB (1) | GB2106996A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5289623A (en) * | 1992-05-28 | 1994-03-01 | Fuji Oozx Inc. | Shim attaching/detaching tool for engine tappet |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20010020925A (en) * | 1999-08-11 | 2001-03-15 | 제이 엘. 차스킨, 버나드 스나이더, 아더엠. 킹 | Nozzle Airfoil Having Movable Nozzle Ribs |
| GB2397855B (en) | 2003-01-30 | 2006-04-05 | Rolls Royce Plc | A turbomachine aerofoil |
| US7104757B2 (en) | 2003-07-29 | 2006-09-12 | Siemens Aktiengesellschaft | Cooled turbine blade |
| GB0418914D0 (en) | 2004-08-25 | 2004-09-29 | Rolls Royce Plc | Turbine component |
| EP1895096A1 (en) * | 2006-09-04 | 2008-03-05 | Siemens Aktiengesellschaft | Cooled turbine rotor blade |
| FR2918105B1 (en) * | 2007-06-27 | 2013-12-27 | Snecma | TURBOMACHINE COOLED AUBE COMPRISING VARIABLE IMPACT REMOTE COOLING HOLES. |
| EP2161411A1 (en) * | 2008-09-05 | 2010-03-10 | Siemens Aktiengesellschaft | Turbine blade with customised natural frequency by means of an inlay |
| US9121288B2 (en) * | 2012-05-04 | 2015-09-01 | Siemens Energy, Inc. | Turbine blade with tuned damping structure |
| GB2518379A (en) * | 2013-09-19 | 2015-03-25 | Rolls Royce Deutschland | Aerofoil cooling system and method |
| US10344619B2 (en) * | 2016-07-08 | 2019-07-09 | United Technologies Corporation | Cooling system for a gaspath component of a gas powered turbine |
| FR3120388A1 (en) * | 2021-03-03 | 2022-09-09 | Safran Aircraft Engines | Rotating blade for an aircraft turbomachine turbine, comprising a flexible passive member for regulating the flow of air for cooling the blade |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1526498A (en) * | 1966-09-14 | 1968-05-24 | Gen Electric | Cooled nozzle for high temperature turbines |
| GB1467483A (en) * | 1974-02-19 | 1977-03-16 | Rolls Royce | Cooled vane for a gas turbine engine |
| GB1530256A (en) * | 1975-04-01 | 1978-10-25 | Rolls Royce | Cooled blade for a gas turbine engine |
| US4128928A (en) * | 1976-12-29 | 1978-12-12 | General Electric Company | Method of forming a curved trailing edge cooling slot |
| GB1552536A (en) * | 1977-05-05 | 1979-09-12 | Rolls Royce | Rotor blade for a gas turbine engine |
-
1981
- 1981-09-30 GB GB08129466A patent/GB2106996A/en not_active Withdrawn
-
1982
- 1982-07-27 JP JP13106882A patent/JPS5867904A/en active Pending
- 1982-09-21 DE DE19823234906 patent/DE3234906A1/en not_active Withdrawn
- 1982-09-28 FR FR8216306A patent/FR2513695A1/en not_active Withdrawn
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5289623A (en) * | 1992-05-28 | 1994-03-01 | Fuji Oozx Inc. | Shim attaching/detaching tool for engine tappet |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2513695A1 (en) | 1983-04-01 |
| DE3234906A1 (en) | 1983-06-01 |
| GB2106996A (en) | 1983-04-20 |
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