JPS58200037A - Diffuser of small size gas turbine - Google Patents
Diffuser of small size gas turbineInfo
- Publication number
- JPS58200037A JPS58200037A JP8428882A JP8428882A JPS58200037A JP S58200037 A JPS58200037 A JP S58200037A JP 8428882 A JP8428882 A JP 8428882A JP 8428882 A JP8428882 A JP 8428882A JP S58200037 A JPS58200037 A JP S58200037A
- Authority
- JP
- Japan
- Prior art keywords
- turbine
- diffuser
- bearing housing
- cylinder
- base portion
- 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
- 238000000034 method Methods 0.000 abstract description 2
- 230000004323 axial length Effects 0.000 abstract 2
- 239000007789 gas Substances 0.000 description 7
- 239000000567 combustion gas Substances 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/026—Shaft to shaft connections
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
本発明は、ガスタービンに用いられる遠心圧縮機のディ
フューザに関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a diffuser for a centrifugal compressor used in a gas turbine.
周知のように、遠心圧縮機は吸込部、羽根車、ディフュ
ーザおよび吐出部から構成され、吸入部から吸込まれた
空気は羽根車に流入し、該羽根車の羽根によって形成さ
れる通路に沿って流れ、羽根車とともに回転して遠心力
の作用で圧縮され、入口より高い圧力となって速度をと
もない羽根車より流出する。そして、羽根車の出口の速
度は大となっているので、ディフューザで速度エネルー
ｔは圧力エネルギに変換される。ディフューザを出た圧
縮空気はスクロールに入り、燃焼器に導かれる。そして
、該遠心圧縮機とタービン車軸は同軸上に隣設され一体
で高速回転する。したがって、ガスタービンは部品点数
が多く、軸方向に長く構成されるので、産業用、殊にビ
ルの地下等に据付ける発電機直結型のガスタービンは難
点を有している。As is well known, a centrifugal compressor is composed of a suction section, an impeller, a diffuser and a discharge section, and the air sucked from the suction section enters the impeller and passes along the path formed by the blades of the impeller. The fluid flows, rotates with the impeller, is compressed by the action of centrifugal force, becomes higher pressure than the inlet, and flows out from the impeller with speed. Since the speed at the outlet of the impeller is high, the speed energy t is converted into pressure energy by the diffuser. Compressed air leaving the diffuser enters the scroll and is directed to the combustor. The centrifugal compressor and the turbine axle are coaxially arranged adjacent to each other and rotate together at high speed. Therefore, a gas turbine has a large number of parts and is long in the axial direction, so that a gas turbine directly connected to a generator for industrial use, especially installed in the basement of a building, has disadvantages.
そこで本発明は、この従来の難点を解消しようとして案
出されたもので、部品点数を節減するとともに軸方向に
短縮するガスタービンを提供しようとするものである。The present invention has been devised to solve these conventional problems, and aims to provide a gas turbine that reduces the number of parts and is shortened in the axial direction.
以下、本発明の実施例にしたかつて説明するか、添付図
面は発電機直結型の小型ガスタービンの要部断面図を示
し、Ａは遠心圧縮機、Ｂは燃焼器、Ｃはタービン翼車を
示す。Hereinafter, an embodiment of the present invention will be described. The attached drawings show a sectional view of the main parts of a small gas turbine directly connected to a generator, in which A is a centrifugal compressor, B is a combustor, and C is a turbine wheel. show.
遠心圧縮機Ａにおいて、１は羽根車、２はディフューザ
、３は吐出部を示し、燃焼器Ｂにおいて、４は燃焼器内
筒、５は燃料噴射弁、６は燃焼器内簡４からタービン翼
車Ｃの初段タービンノズル７へ燃焼ガスを導入する流路
及び吐出部３から燃焼器内筒４へ圧縮空気を導入する流
路を形成するスクロールを示し、タービン翼車Ｃにおい
て、８は初段パケット、９は第２段タービンノズル、１
０は第２段パケット、１１は排気ケーシング、１２はタ
ービン車軸を示し、該車軸は後述のタービン側軸受ハウ
ジングと圧縮機側軸受ハウジングとで支承されている。In the centrifugal compressor A, 1 is the impeller, 2 is the diffuser, and 3 is the discharge part. In the combustor B, 4 is the combustor inner cylinder, 5 is the fuel injection valve, and 6 is the combustor inner cylinder 4 to the turbine blade. This figure shows a scroll that forms a flow path for introducing combustion gas into the first-stage turbine nozzle 7 of the vehicle C and a flow path for introducing compressed air from the discharge part 3 into the combustor inner cylinder 4. In the turbine wheel C, 8 is a first-stage packet. , 9 is the second stage turbine nozzle, 1
0 is a second stage packet, 11 is an exhaust casing, and 12 is a turbine axle, which is supported by a turbine-side bearing housing and a compressor-side bearing housing, which will be described later.
次に、ディフューザ２は、その基部をコーン状支持体１
３と一体的に構成され、該支持体１３はその基部を円筒
体１４と連設して、タービン側軸受ハウジングを形成し
ている。円筒体１４の端面には初段タービンノズル７の
基部が固着されている。また、円筒体１４内・にはター
ビン車軸１２か挿通されているが、両者の間には、中央
にコロ軸受１５が介在され、その片側にラビリンスシー
ル１６が介在されている。ｉ７はメタルを示す。Next, the diffuser 2 has its base connected to the cone-shaped support 1
The support body 13 has its base connected to the cylindrical body 14 to form a turbine-side bearing housing. The base of the first-stage turbine nozzle 7 is fixed to the end face of the cylindrical body 14 . Further, a turbine axle 12 is inserted into the cylindrical body 14, and a roller bearing 15 is interposed in the center between the two, and a labyrinth seal 16 is interposed on one side of the roller bearing 15. i7 indicates metal.
以上のようなｍ１ｆｆｌになっているので、吸入部から
吸込まれた空気は羽根車１に流入し、該羽根車１の羽根
によって形成される通路に沿って流れ、羽根車１ととも
に回転して遠心力の作用で圧縮され、入−口より高い圧
力となって速度を伴い羽根車１より流出する。そして、
吐出部３の速度は大となっているので、ディフューザ２
で速度エネルギは圧力エネルギに変換される。ディフュ
ーザ２を出た圧縮空気はスクロール６の外周に入り、燃
焼器Ｂに導かれる。燃焼器Ｂの内筒４で、燃料噴射弁５
より燃料を噴射し、燃焼させて高圧の燃焼ガスを形成す
る。該燃焼ガスはスクロール６の内周で案内されて、初
段タービンノズル７へ導入され、タービンの段ごとで圧
力が降下し、速度エネルギに変換されながらタービン車
軸１１を高速回転させる。Since the m1ffl is as above, the air sucked from the suction part flows into the impeller 1, flows along the path formed by the blades of the impeller 1, rotates with the impeller 1, and is centrifuged. It is compressed by the action of the force, becomes higher pressure than the inlet, and flows out from the impeller 1 with speed. and,
Since the speed of the discharge part 3 is high, the diffuser 2
Velocity energy is converted to pressure energy. Compressed air leaving the diffuser 2 enters the outer periphery of the scroll 6 and is guided to the combustor B. In the inner cylinder 4 of the combustor B, the fuel injection valve 5
The fuel is injected and combusted to form high-pressure combustion gas. The combustion gas is guided by the inner periphery of the scroll 6 and introduced into the first stage turbine nozzle 7, and the pressure decreases at each stage of the turbine, causing the turbine axle 11 to rotate at high speed while being converted into velocity energy.
以上要するに本発明は、タービン車軸が圧縮機側の軸受
ハウジングとタービン側の軸受ハウジングで支承され前
記遠心圧縮機の羽根車外側に設けたディフューザの基部
を、初段タービンノズルの基部が固着され且つタービン
車軸が挿通されたタービン側軸受ハウジングより延設し
た小型がスタービンのディフューザであるから、次の効
果を奏する。In summary, the present invention provides a turbine axle shaft supported by a bearing housing on the compressor side and a bearing housing on the turbine side, and a base of a diffuser provided outside the impeller of the centrifugal compressor, the base of the first stage turbine nozzle is fixed, and Since the small diffuser of the turbine extends from the turbine-side bearing housing through which the axle is inserted, the following effects are achieved.
■ 従来のガスタービンでは、ディフューザ、軸受ハウ
ジング、車軸等部品点数かあったが、本発明ではディフ
ューザと軸受／％ウジングとを一体に構成したので、こ
れら点数を少なくすることができる。(2) Conventional gas turbines have a number of parts such as a diffuser, a bearing housing, and an axle, but in the present invention, the diffuser and bearing/% housing are integrated, so the number of these parts can be reduced.
■ タービン車軸が圧縮機側の軸受ノ１ウジングとター
ビン側軸受ハウジングとで支承されて簡素化されており
、しかも、ディフューザの芯出を必要としているので、
高速回転するガスタービンには好都合となる。■ The turbine axle is supported by the bearing housing on the compressor side and the bearing housing on the turbine side, which simplifies the process.Moreover, centering of the diffuser is required.
This is convenient for gas turbines that rotate at high speed.
■ ディフューザ用軸受がないので、軸方向に短縮でき
る。■ Since there is no diffuser bearing, it can be shortened in the axial direction.
添付図面は本発明の実施例の断面図をなす。
１・・・羽根車、２・・・ディフューザ、７・・・初段
タービンノズル、１２・・・タービン車軸、１３・・・
コーン状支持体、１４・・・円筒体、１５・・・コロ軸
受。
代理人 弁理土間 部 吉 彦The accompanying drawings represent cross-sectional views of embodiments of the invention. DESCRIPTION OF SYMBOLS 1... Impeller, 2... Diffuser, 7... First stage turbine nozzle, 12... Turbine axle, 13...
Cone-shaped support, 14... Cylindrical body, 15... Roller bearing. Agent: Yoshihiko Domabe, Patent Attorney
Claims (1)
受ハウジングとで支承され、前記遠心式の圧縮機の羽根
車外側に設けたディフューザの基部を、初段タービンノ
ズルの基部が固着された前記タービン側軸受ハウジング
より延出した小型ガスタービンのディフューザ。The turbine axle is supported by the compressor side bearing housing and the turbine side bearing housing, and the base of the diffuser provided outside the impeller of the centrifugal compressor is fixed to the turbine side bearing housing. The diffuser of a small gas turbine extends further.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8428882A JPS58200037A (en) | 1982-05-18 | 1982-05-18 | Diffuser of small size gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8428882A JPS58200037A (en) | 1982-05-18 | 1982-05-18 | Diffuser of small size gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS58200037A true JPS58200037A (en) | 1983-11-21 |
Family
ID=13826275
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP8428882A Pending JPS58200037A (en) | 1982-05-18 | 1982-05-18 | Diffuser of small size gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS58200037A (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS55151122A (en) * | 1979-05-16 | 1980-11-25 | Avco Corp | Structure of bleeding hole in tip of blade of diffuser with automatic ejector controller |
| JPS5733B2 (en) * | 1978-05-04 | 1982-01-05 |
-
1982
- 1982-05-18 JP JP8428882A patent/JPS58200037A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5733B2 (en) * | 1978-05-04 | 1982-01-05 | ||
| JPS55151122A (en) * | 1979-05-16 | 1980-11-25 | Avco Corp | Structure of bleeding hole in tip of blade of diffuser with automatic ejector controller |
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