JPH0381502A - Sector wheel of radial gas turbine - Google Patents
Sector wheel of radial gas turbineInfo
- Publication number
- JPH0381502A JPH0381502A JP21600089A JP21600089A JPH0381502A JP H0381502 A JPH0381502 A JP H0381502A JP 21600089 A JP21600089 A JP 21600089A JP 21600089 A JP21600089 A JP 21600089A JP H0381502 A JPH0381502 A JP H0381502A
- Authority
- JP
- Japan
- Prior art keywords
- sector wheel
- fan
- air
- flow path
- gas turbine
- 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
- 238000001816 cooling Methods 0.000 claims abstract description 13
- 230000008878 coupling Effects 0.000 claims description 6
- 238000010168 coupling process Methods 0.000 claims description 6
- 238000005859 coupling reaction Methods 0.000 claims description 6
- 230000006835 compression Effects 0.000 claims description 2
- 238000007906 compression Methods 0.000 claims description 2
- 230000000903 blocking effect Effects 0.000 abstract 2
- 239000007789 gas Substances 0.000 description 40
- 238000010586 diagram Methods 0.000 description 8
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 5
- 238000005192 partition Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000007664 blowing Methods 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000002250 progressing effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
（産業上の利用分野）
この発明は、ラジアルガスタービンの扇単に開し、空気
冷却することにより翼車の耐熱性を向上させ、−層高温
のガスを作用させてラジアルガスタービンの熱効率を高
めるのに利用できる発明である。[Detailed Description of the Invention] (Industrial Application Field) This invention improves the heat resistance of the impeller by opening the fan of a radial gas turbine and cooling it with air. This invention can be used to increase the thermal efficiency of radial gas turbines.
（従来の技術）
ラジアルガスタービンは、第８図に略示するように、コ
ンプレッサ１で圧縮した圧縮空気２と燃料３とを燃焼器
４に入れて燃焼させ、得られた高温の作用ガス５をラジ
アルガスタービン６に供給し扇車７を回転させて動力を
得る装置である。第９図はラジアルガスタービンの扇車
７を例示する。(Prior Art) As schematically shown in FIG. 8, a radial gas turbine is constructed by putting compressed air 2 compressed by a compressor 1 and fuel 3 into a combustor 4 and burning the resulting high-temperature working gas 5. This device supplies power to a radial gas turbine 6 and rotates a fan wheel 7 to obtain power. FIG. 9 illustrates a fan wheel 7 of a radial gas turbine.
ガスタービンの熱効率は作用ガスの温度が高いほど良く
なるが、使用材料の耐熱性能に限度があるため、作用ガ
ス温度のみを一方的に高くすることはできない。The thermal efficiency of a gas turbine improves as the temperature of the working gas increases, but because there is a limit to the heat resistance of the materials used, it is not possible to unilaterally increase the temperature of the working gas.
そこで耐熱強度の大きな材料の開発を進める一方で、最
も高熱の影響を受けるタービン翼を空気冷却してその温
度を翼材料の耐熱強度範囲内に抑えるようにすることが
軸流型のガスタービンでは普通に行なわれて来ている。Therefore, while progressing with the development of materials with high heat resistance, it is important for axial flow gas turbines to air cool the turbine blades, which are most affected by high heat, to keep the temperature within the heat resistance range of the blade material. It is commonly practiced.
これによって作用ガス温度を９５０℃→１３５０℃まで
逐次高めることができるようになって来た。As a result, it has become possible to gradually increase the working gas temperature from 950°C to 1350°C.
軸流型ガスタービンでは、コンプレッサて得た圧縮空気
の１０〜１５％を使用して翼冷却を行なっているが、ラ
ジアルガスタービンでは翼の形状が複雑なこともあって
Ｒ冷却は行なわれておらず、耐熱性の大きいセラミック
を使用して熱効率を高めようとする方向に研究が進めら
れている状況である。In axial flow gas turbines, 10 to 15% of the compressed air obtained from the compressor is used to cool the blades, but in radial gas turbines, R cooling is not performed because the blade shape is complex. However, research is currently underway in the direction of increasing thermal efficiency by using highly heat-resistant ceramics.
（発明が解決しようとする課題）
この発明は、−層高部の作用カスの使用がてきるように
、ラジアルガスタービンの扇車を空気冷却できる構造と
して、ラジアルカスタービンの熱効率を高めようとする
ものである。(Problems to be Solved by the Invention) This invention aims to improve the thermal efficiency of a radial gas turbine by creating a structure in which the fan of the radial gas turbine can be air-cooled so that the working waste in the high layer can be used. It is something to do.
（課題を解決するための手段）
この発明は、円錐板状のラジアルガスタービンの扇車の
背面に、多数のフィン及びカバーにより放射方向に仕切
られた空気流路を形成し、この流路に送入した圧縮空気
を多数の小孔を通して、燃焼ガスの流れる扇車の表面に
流出させ、又、扇車の表面に突出形成した翼を中空にし
側面に多数の小孔を穿設して、翼内に送り込んだ圧縮空
気をこの小孔から流出するようにしたものである。(Means for Solving the Problems) This invention forms an air flow path partitioned in the radial direction by a large number of fins and covers on the back side of a fan of a conical plate-shaped radial gas turbine. The compressed air sent in is passed through a large number of small holes and flows out onto the surface of a fan through which combustion gas flows, and the blades protruding from the surface of the fan are made hollow and a large number of small holes are bored on the side. The compressed air sent into the blade is made to flow out through this small hole.
（作 用）
扇車の裏面に設けた、多数のフィンによって区切られた
流路を通って多数の小孔から扇車の表面に流出する空気
は、扇車の裏面、小孔壁及びフィンに接触して扇車を冷
却し、小孔から流出した後は扇車の表面に沿って流れ、
この表面に空気による熱遮断膜を形成して扇車が高温ガ
ス流により熱せられる程度を小さくし、又、扇車の表面
に突出形成された中空の翼に流入した空気は、翼を内部
から冷却すると共にその側面の小孔から流出して翼に沿
う熱遮断膜を形成して翼が加熱される程度を小さくする
。(Function) The air flowing out from the many small holes to the surface of the fan through the flow channels separated by the many fins provided on the back of the fan flows to the back of the fan, the small hole walls, and the fins. It cools the fan wheel by contact, and after flowing out from the small hole, it flows along the surface of the fan wheel,
A heat shielding film made of air is formed on this surface to reduce the degree to which the fan is heated by the high-temperature gas flow, and the air that flows into the hollow blades formed protruding from the surface of the fan causes the blades to be heated from the inside. As it cools, it flows out through small holes on its side, forming a heat shielding film along the blade, reducing the degree to which the blade is heated.
（実施例）
第１〜７図は本発明の実施例を示し、第１図は扇車の半
部縦断面図、第２図は第１図のＡ−Ａ断面部分図、第３
図は扇車の部分背面図、第４図は第２図のＢ−Ｂ断面部
分図、第５図は圧縮空気を冷却しないで使用する場合の
空気、ガス等の流れを示す略図、第６図は圧縮空気を大
気で冷却する場合の同様の略図、第７図は圧縮空気を水
で冷却する熱交換器の略図である。(Example) Figures 1 to 7 show examples of the present invention, in which Figure 1 is a longitudinal cross-sectional view of a half part of a fan, Figure 2 is a partial cross-sectional view taken along line AA in Figure 1, and Figure 3 is a partial longitudinal cross-sectional view of a fan wheel.
The figure is a partial rear view of the fan, Figure 4 is a partial cross-sectional view taken along line B-B in Figure 2, Figure 5 is a schematic diagram showing the flow of air, gas, etc. when compressed air is used without cooling, and Figure 6 is a partial rear view of the fan. The figure is a similar schematic diagram for cooling compressed air with the atmosphere, and FIG. 7 is a schematic diagram of a heat exchanger for cooling compressed air with water.
扇車７の表面には、第９図の従来例と同様に、複数の屈
曲した翼８（第１図には、判り易くするため、翼を放射
方向に真直なものとして示している）が突出して形成さ
れており、裏面には第３図のように放射方向に複数のフ
ィン９が突出形成されている。フィン９の間には多数の
小孔１０が表面の翼８の間に開口させて穿設されている
。フィン９の突端を連ねながらこれを覆って扇車の背面
にカバー１１が設けられており、カバー１１、フィン９
、扇車７の間に第一流路１２か形成されている。カバー
１１の外方には、それぞれ扇車７に固定された円板状の
第一隔壁１３、第二隔壁１４により第二流路１５が形成
されている。第二流路１５は周端部において第一流路１
２に通じている。カバー１１、両隅壁１３．１４を取付
けた扇車７は、ケーシング１６で覆われ、翼８の周端部
に静Ｒ（図示せず）の形成するノズルにより方向が最適
となるように整流された作用ガス５を吹込むガス人口１
７を開設する。第二流路１５へは、扇車７の軸部１８内
に設けた軸部向流路１９、環状溝２０、カップリング２
１を通して圧縮空気２を供給する。On the surface of the fan wheel 7, a plurality of bent blades 8 (in FIG. 1, the blades are shown as being straight in the radial direction for ease of understanding) are provided, as in the conventional example shown in FIG. It is formed to protrude, and a plurality of fins 9 are formed protruding from the back surface in the radial direction as shown in FIG. A large number of small holes 10 are opened between the fins 9 and between the blades 8 on the surface. A cover 11 is provided on the back of the fan wheel so as to connect and cover the tips of the fins 9, and the cover 11 and the fins 9
, a first flow path 12 is formed between the fan wheels 7. A second flow path 15 is formed on the outside of the cover 11 by a disk-shaped first partition wall 13 and a second partition wall 14, which are each fixed to the fan wheel 7. The second flow path 15 is connected to the first flow path 1 at the peripheral end.
It leads to 2. The fan wheel 7 with the cover 11 and both corner walls 13 and 14 attached is covered with a casing 16, and a nozzle formed by a static R (not shown) at the peripheral end of the blade 8 rectifies the flow so that the direction is optimal. Gas population 1 injecting working gas 5
7 will be established. The second flow path 15 is connected to a shaft direction flow path 19 provided in the shaft portion 18 of the fan wheel 7, an annular groove 20, and a coupling 2.
Compressed air 2 is supplied through 1.
翼８は、第２図、第４図のように中空になっていて、内
部にフィン２２．２２を設け、側面に小孔２３を穿設し
ている。The wing 8 is hollow as shown in FIGS. 2 and 4, and has fins 22, 22 provided inside and a small hole 23 bored in the side surface.
カップリング２１から扇車内に吹込む冷却用空気２は、
第５図に示すようにコンプレッサ１において圧縮し温度
上昇した空気２（例えば２０℃の大気を圧縮比７で圧縮
すると２９４℃となる。）の一部（１０〜１５％）をそ
のまま使用することも考えられるが、第６図のようにこ
の空気を熱交換器２４を通して４０〜５０℃の低温空気
２ａとして使用すれば、冷却効果を一層高めることが出
来る。The cooling air 2 blown into the fan from the coupling 21 is
As shown in Fig. 5, a part (10 to 15%) of the air 2 whose temperature has been increased by compressing it in the compressor 1 (for example, when air at 20°C is compressed at a compression ratio of 7, the temperature becomes 294°C) is used as is. However, if this air is passed through a heat exchanger 24 and used as low-temperature air 2a of 40 to 50°C as shown in FIG. 6, the cooling effect can be further enhanced.
熱交換器２４としては、第６図のように、空気管２５を
大気で冷却するもの、第７図のように、ポンプ２６によ
り水を通ず水管２７と空気管２５との間で熱交換するも
の等が使用できる。As shown in FIG. 6, the heat exchanger 24 cools the air pipe 25 with the atmosphere, and as shown in FIG. 7, it uses a pump 26 to exchange heat between the water pipe 27 and the air pipe 25 without passing water. You can use those that do.
以上のように構成するから、ガス人口１７から燃焼器４
を出た高温の作用ガス５を吹込むと、ガス５は翼８に沿
って翼間流路２８を流れつつ翼８を横に押して扇車７を
回転させ、この回転は扇単に固定した軸２９から取出さ
れる。Since the configuration is as described above, from the gas population 17 to the combustor 4
When high temperature working gas 5 is blown in, the gas 5 flows along the blades 8 through the inter-blade flow path 28 and pushes the blades 8 sideways to rotate the fan wheel 7, and this rotation is caused by a shaft fixed to the fan wheel. 29.
方、固定のカップリング２１から回転する扇車の軸部１
８に設けた軸部向流路１９に吹込まれた冷却用空気は、
第二流路１５に入って扇車の周端部に進み、続いて一方
では第一流路１２に入り、他方では通孔３０から翼８．
８内に形成された翼内流路８ａに流入する。第一流路１
２に入った空気は、扇車の背面やフィン９．９に接触し
てこれらを冷却した後、小孔１０．１０から作用ガスの
流れる翼間流路２８に流出し、ガス流に押されて扇車表
面に沿って流れ、扇車表面に断熱性の空気膜を形成して
扇車表面が高温の作用ガスのため加熱される程度小さく
する。翼間流路２８に流出した空気は、作用ガスと共に
排出される。On the other hand, the fan shaft 1 rotates from a fixed coupling 21.
The cooling air blown into the shaft counter-flow path 19 provided at 8 is
It enters the second flow channel 15 and proceeds to the circumferential edge of the fan wheel, then on the one hand enters the first flow channel 12 and on the other hand through the through hole 30 to the blade 8.
The air flows into an intra-blade flow path 8a formed in the blade 8. First flow path 1
The air that has entered 2 contacts the back of the fan and the fins 9.9 to cool them, and then flows out from the small hole 10.10 into the interblade flow path 28 through which the working gas flows, and is pushed by the gas flow. The air flows along the surface of the fan, forming an insulating air film on the surface of the fan, reducing the extent to which the surface of the fan is heated by the high-temperature working gas. The air flowing out into the interblade flow path 28 is discharged together with the working gas.
通孔３０から翼内流路８ａに入った空気は、中空の翼内
面やフィン２２に接触して翼を冷却すると共に小孔２３
から作用ガスの流れる翼間流路２８に流出し、翼の外面
に空気による熱遮断膜を形成して翼が高温の作用ガスの
ため加熱される程度を小さくし、その後作用ガスと共に
排出される。The air that enters the inner blade flow path 8a from the through hole 30 contacts the hollow inner surface of the blade and the fins 22 to cool the blade, and also flows through the small holes 23.
The air flows out into the inter-blade flow path 28 through which the working gas flows, forms a heat-insulating film of air on the outer surface of the blade, reduces the degree to which the blade is heated by the high-temperature working gas, and is then discharged together with the working gas. .
このようにしてカップリング２１からン令却用の圧縮空
気を吹込むことにより、扇車を表裏から冷却することが
できる。By blowing cooling compressed air from the coupling 21 in this manner, the fan wheel can be cooled from the front and back.
（発明の効果）
扇車内に冷却用空気流路を構成した結果、高温の作用ガ
スのため加熱されることの著しい翼及び翼車壁を冷却し
、又熱遮断膜を形成して加熱程度を低くするから、その
分、作用ガスの温度を高くしてラジアルガスタービンの
熱効率を高めることができる。(Effects of the invention) As a result of configuring the cooling air flow path inside the fan, the blades and the blade wheel wall, which are often heated due to high temperature working gas, are cooled, and a heat shielding film is formed to reduce the degree of heating. Since the temperature is lowered, the temperature of the working gas can be increased accordingly, thereby increasing the thermal efficiency of the radial gas turbine.
第１〜７図は本発明の実施例を示し、第１図は扇車の半
部縦断面図、第２図は第１図のＡ−Ａ断面部分図、第３
図は扇車の部分背面図、第４図は第２図のＢ−Ｂ断面部
分図、第５図は圧縮空気を冷却しないで使用する場合の
ガスタービンの構成を示す略図、第６図は圧縮空気を大
気で冷却する場合の同様の略図、第７図は圧縮空気を水
で冷却する熱交換器の略図、第８図は従来のガスタービ
ンの構成を示す略図、第９図は従来のラジアルガスター
ビンの扇車を例示する斜視図である。
１：コンプレッサ、２：圧縮空気、２ａ：低温空気、３
：燃料、４：燃焼器、５：作用ガス、６ラジアルガスタ
ービン、７：扇車、８：Ｒ１８ａ 翼内流路、９：フィ
ン、１０：小孔、１１カバー、１２：第一流路、１３：
第一隔壁、１４：第二隔壁、１５：第二流路、１６：ケ
ーシング、１７：ガス入口、１８：軸部、１９：軸部向
流路、２０：環状溝、２１：カップリング、２２フイン
、２３：小孔、２４．熱交換器、２５空気管、２６・ポ
ンプ、２７：水管、２８：翼間流路、２９．軸、３０：
通孔。
１４−1 to 7 show embodiments of the present invention, in which FIG. 1 is a longitudinal cross-sectional view of half a fan wheel, FIG. 2 is a partial cross-sectional view taken along the line AA in FIG.
The figure is a partial rear view of the fan, Figure 4 is a partial cross-sectional view taken along line B-B in Figure 2, Figure 5 is a schematic diagram showing the configuration of a gas turbine when compressed air is used without cooling, and Figure 6 is A similar diagram when compressed air is cooled by the atmosphere, Figure 7 is a diagram of a heat exchanger that cools compressed air with water, Figure 8 is a diagram showing the configuration of a conventional gas turbine, and Figure 9 is a diagram of a conventional gas turbine. 1 is a perspective view illustrating a fan wheel of a radial gas turbine. 1: Compressor, 2: Compressed air, 2a: Low temperature air, 3
: fuel, 4: combustor, 5: working gas, 6 radial gas turbine, 7: fan, 8: flow path in R18a blade, 9: fin, 10: small hole, 11 cover, 12: first flow path, 13 :
First partition, 14: Second partition, 15: Second passage, 16: Casing, 17: Gas inlet, 18: Shaft, 19: Shaft counterflow passage, 20: Annular groove, 21: Coupling, 22 Fin, 23: small hole, 24. Heat exchanger, 25 Air pipe, 26 Pump, 27: Water pipe, 28: Inter-blade flow path, 29. Axis, 30:
Through hole. 14-
Claims (1)
）を放射方向に突出形成し、このフィン及びフィン端を
連ねるカバー（１１）により放射方向に仕切られた第一
流路（１２）を形成し、この流路を多数の小孔（１０）
により扇車の表面に通じさせ、扇車の表面に突出形成し
た翼（８）を中空にして翼内流路（８ａ）を形成すると
共に、この流路内にフィン（２２）を設け、翼（８）の
側面に多数の小孔（２３）を穿設し、前記の扇車背面の
第一流路（１２）及び翼内流路（８ａ）に扇車の軸部を
介して冷却用圧縮空気を送るカップリング（２１）、軸
部内流路（１９）、半径方向の第二流路（１５）を設け
たラジアルガスタービンの扇車。(1) Many fins (9) on the back of the conical fan wheel (7).
) are formed to protrude in the radial direction, and a first flow path (12) partitioned in the radial direction by a cover (11) connecting the fins and the fin ends is formed, and this flow path is connected to a large number of small holes (10).
The blades (8) protruding from the surface of the fan are made hollow to form an internal flow path (8a), and fins (22) are provided in this flow path. A large number of small holes (23) are bored in the side of the fan (8), and cooling compression is applied to the first flow path (12) on the back of the fan and the flow path (8a) in the blade through the shaft of the fan. A fan wheel of a radial gas turbine provided with a coupling (21) for sending air, a channel in the shaft (19), and a second channel in the radial direction (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP21600089A JPH0381502A (en) | 1989-08-24 | 1989-08-24 | Sector wheel of radial gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP21600089A JPH0381502A (en) | 1989-08-24 | 1989-08-24 | Sector wheel of radial gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0381502A true JPH0381502A (en) | 1991-04-05 |
Family
ID=16681736
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP21600089A Pending JPH0381502A (en) | 1989-08-24 | 1989-08-24 | Sector wheel of radial gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0381502A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10029807C1 (en) * | 2000-06-16 | 2002-03-21 | Daimler Chrysler Ag | Exhaust gas turbocharger for IC engine has turbine wheel provided with hollow space between hub base and hub envelope |
| KR20030076848A (en) * | 2002-03-23 | 2003-09-29 | 조형희 | Combustor liner of a gas turbine engine using impingement/effusion cooling method with pin-fin |
| JP2008519192A (en) * | 2004-11-02 | 2008-06-05 | アルストム テクノロジー リミテッド | Optimal turbine stage of turbine apparatus and method for configuring turbine stage |
-
1989
- 1989-08-24 JP JP21600089A patent/JPH0381502A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10029807C1 (en) * | 2000-06-16 | 2002-03-21 | Daimler Chrysler Ag | Exhaust gas turbocharger for IC engine has turbine wheel provided with hollow space between hub base and hub envelope |
| KR20030076848A (en) * | 2002-03-23 | 2003-09-29 | 조형희 | Combustor liner of a gas turbine engine using impingement/effusion cooling method with pin-fin |
| JP2008519192A (en) * | 2004-11-02 | 2008-06-05 | アルストム テクノロジー リミテッド | Optimal turbine stage of turbine apparatus and method for configuring turbine stage |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US2779565A (en) | Air cooling of turbine blades | |
| JP2505693B2 (en) | Gas turbine | |
| US3388888A (en) | Cooled turbine nozzle for high temperature turbine | |
| JP2002534627A (en) | Recuperator for gas turbine engine | |
| US3999377A (en) | Tesla-type turbine with alternating spaces on the rotor of cooling air and combustion gases | |
| US3831374A (en) | Gas turbine engine and counterflow heat exchanger with outer air passageway | |
| US3528751A (en) | Cooled vane structure for high temperature turbine | |
| JP2006509370A5 (en) | ||
| JPH07208106A (en) | Turbine | |
| CN106460550A (en) | Gas turbine engine with rotor centered cooling system in exhaust diffuser | |
| JPS61197702A (en) | Gas turbine engine | |
| US2407164A (en) | Internal-combustion turbine | |
| JP2006504024A (en) | Passive cooled blade platform | |
| US4358926A (en) | Turbine engine with shroud cooling means | |
| JP2642748B2 (en) | Combustion air blower | |
| US3252506A (en) | Rotary heat exchanger | |
| JP2003520315A (en) | Gas turbine engine | |
| CN220286056U (en) | Semiconductor control-containing inner channel casing structure | |
| JPH09507550A (en) | Gas turbine blade with high cooling efficiency | |
| US3252505A (en) | Rotary heat exchanger | |
| JPH0510102A (en) | Gas turbine blade and gas turbine device | |
| JPS59153902A (en) | Effectively cooled blade | |
| CN116792798B (en) | Fume exhauster | |
| JPS6143944Y2 (en) | ||
| JPH116445A (en) | Gas turbine engine |