JPH09250353A - Cooling device of turbine rotor - Google Patents
Cooling device of turbine rotorInfo
- Publication number
- JPH09250353A JPH09250353A JP5484496A JP5484496A JPH09250353A JP H09250353 A JPH09250353 A JP H09250353A JP 5484496 A JP5484496 A JP 5484496A JP 5484496 A JP5484496 A JP 5484496A JP H09250353 A JPH09250353 A JP H09250353A
- Authority
- JP
- Japan
- Prior art keywords
- turbine
- turbine rotor
- pressure gas
- lubricating oil
- back surface
- 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
Landscapes
- Supercharger (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明はガスタービン又はタ
ーボチャージャー等のように高温ガスを作動流体とする
ターボ機械に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbomachine, such as a gas turbine or a turbocharger, which uses a high temperature gas as a working fluid.
【０００２】[0002]
【従来の技術】従来のものを図２に基づいて説明する。
タービンケーシング５内のスクロール４にて導かれた高
温高圧ガスは、タービン動翼３へ流入し、タービンロー
タ１ａを回転させ、その回転出力は同タービンロータ１
ａの他端で図示省略のコンプレッサー及び発電機等へ接
続されている。2. Description of the Related Art A conventional device will be described with reference to FIG.
The high-temperature high-pressure gas guided by the scroll 4 in the turbine casing 5 flows into the turbine rotor blades 3 to rotate the turbine rotor 1a, and the rotational output thereof is the same.
The other end of a is connected to a compressor, a generator, etc. not shown.
【０００３】なお１ｂはタービンロータ背面部、２はピ
ストンリング、６はタービン背板、７ａ，７ｂはタービ
ンロータ１ａのジャーナル軸受、８は軸受台、また、９
はＶバンドカップリングを示す。Reference numeral 1b is a turbine rotor rear surface, 2 is a piston ring, 6 is a turbine back plate, 7a and 7b are journal bearings of the turbine rotor 1a, 8 is a bearing stand, and 9
Indicates V band coupling.
【０００４】[0004]
【発明が解決しようとする課題】前記した従来のもので
は、高温高圧ガスは、タービンロータ背面部１ｂに設置
されたピストンリング２にてシールされ、軸受台８内部
へ流入しない様になっているが、タービン背板６とター
ビン動翼３のすき間に流入する前記高温高圧ガス及び加
熱されたタービン動翼３からの熱伝達により、ピストン
リング２部はかなりの高温となり、運転時間と共にピス
トンリング２の変形等を引き起こし、シールの役目を果
さなくなり最悪の場合には、タービンロータ背面部１ｂ
等の焼付きを起こし、トラブルの原因となることがあ
る。In the above-mentioned conventional one, the high-temperature high-pressure gas is sealed by the piston ring 2 installed on the turbine rotor rear surface 1b so as not to flow into the bearing base 8. However, due to the high-temperature high-pressure gas flowing into the gap between the turbine back plate 6 and the turbine rotor blade 3 and the heat transfer from the heated turbine rotor blade 3, the piston ring 2 portion becomes considerably hot, and the piston ring 2 becomes hot with the operation time. In the worst case, the turbine rotor rear surface portion 1b
It may cause seizure, etc., causing troubles.
【０００５】本発明はこのような不具合を解消し、高温
高圧ガスによる温度上昇を抑え、安定性に富んだものを
提供することを課題とするものである。An object of the present invention is to solve the above problems, to suppress the temperature rise due to the high temperature and high pressure gas, and to provide a highly stable product.
【０００６】[0006]
【課題を解決するための手段】本発明は前記した課題を
解決するべくなされたもので、高温高圧ガスを作動流体
とする半径流ガスタービン又はターボチャージャー等の
ターボ機械において、タービンロータ背面部に向けて軸
受け潤滑油の一部を噴射する噴射ノズルを設けてなるタ
ービンロータの冷却装置を提供し、作動流体である高温
高圧ガスの影響で高温化するタービンロータ背面部に、
軸受け潤滑油の一部を噴射ノズルで噴射して強制的に冷
却することにより、同タービンロータ背面部の温度上昇
を抑制し、変形等を防止するようにしたものである。SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and in a turbomachine such as a radial flow gas turbine or a turbocharger using a high-temperature high-pressure gas as a working fluid, a turbine rotor rear surface portion is provided. Provided is a turbine rotor cooling device provided with an injection nozzle for injecting a part of the bearing lubricating oil toward a turbine rotor rear surface that is heated by the influence of high-temperature high-pressure gas that is a working fluid.
By injecting a part of the bearing lubricating oil with an injection nozzle to forcibly cool it, the temperature rise of the turbine rotor rear surface part is suppressed and deformation and the like are prevented.
【０００７】[0007]
【発明の実施の形態】本発明の実施の一形態を図１に基
づいて説明する。なお、前記した従来のものと同一の部
分については図中同一の符号を付して示し、説明を簡明
にするため重複する説明は省略する。BEST MODE FOR CARRYING OUT THE INVENTION An embodiment of the present invention will be described with reference to FIG. It should be noted that the same parts as those of the above-described conventional one are denoted by the same reference numerals in the drawings, and duplicated description will be omitted for the sake of simplicity.
【０００８】即ち、本実施の形態では、軸受台８に設け
られている軸受潤滑油の給油孔１０に連通してノズル噴
射用給油孔１１を設け、その先端には、タービンロータ
背面部１ｂへ向けて開孔する噴射孔１２ａを有する噴射
ノズル１２を設置している。That is, in the present embodiment, a nozzle injection oil supply hole 11 is provided so as to communicate with the bearing lubricating oil supply hole 10 provided in the bearing base 8, and the tip thereof is connected to the turbine rotor rear surface 1b. An injection nozzle 12 having an injection hole 12a that opens toward the front is installed.
【０００９】従って給油孔１０から供給される軸受潤滑
油の一部が噴射ノズル１２の噴射孔１２ａからタービン
ロータ背面部１ｂへ噴射され、同タービンロータ背面部
１ｂが作動流体である高温高圧ガスの熱影響を受け温度
上昇してピストンリング２が変形するのを防止し、シー
ル機能を確実に維持させ、またタービンロータ背面部１
ｂが焼きつきをおこす心配を無くするものである。Therefore, a part of the bearing lubricating oil supplied from the oil supply hole 10 is injected from the injection hole 12a of the injection nozzle 12 to the turbine rotor back surface 1b, and the turbine rotor back surface 1b of the high temperature high pressure gas as a working fluid. The piston ring 2 is prevented from being deformed due to the temperature rise due to heat influence, and the sealing function is reliably maintained.
This eliminates the fear that b will cause burn-in.
【００１０】以上、本発明を図示の実施の形態について
説明したが、本発明はかかる実施の形態に限定されず、
本発明の範囲内でその具体的構造に種々の変更を加えて
よいことはいうまでもない。Although the present invention has been described above with reference to the illustrated embodiments, the present invention is not limited to such embodiments.
It goes without saying that various modifications may be made to the specific structure within the scope of the present invention.
【００１１】[0011]
【発明の効果】以上本発明によれば、潤滑油が噴射ノズ
ルにより、タービンロータ背面部へ噴射されることによ
り、同タービンロータ背面部が高温高圧ガスにより温度
上昇するのを抑制し、タービンロータ背面部及びその近
傍に配設される関連部材の変形等を防止することによ
り、ノンメンテナンスで長時間の運転を可能とし、安定
した装置を得ることができたものである。As described above, according to the present invention, the lubricating oil is injected by the injection nozzle to the back surface of the turbine rotor, thereby suppressing the temperature rise of the back surface of the turbine rotor due to the high-temperature high-pressure gas. By preventing deformation of the related members arranged on the back surface and in the vicinity thereof, long-term operation can be performed without maintenance and a stable device can be obtained.
【図１】本発明の実施の一形態に係るガスタービンの断
面図。FIG. 1 is a cross-sectional view of a gas turbine according to an embodiment of the present invention.
【図２】従来のガスタービンの断面図。FIG. 2 is a sectional view of a conventional gas turbine.
１ａ タービンロータ １ｂ タービンロータ背面部 ２ ピストンリング ３ タービン動翼 ４ タービンスクロール ５ タービンケーシング ６ タービン背板 ８ 軸受台 １０ 給油孔 １１ ノズル噴射用給油孔 １２ 噴射ノズル １２ａ 噴射孔 1a Turbine rotor 1b Turbine rotor back part 2 Piston ring 3 Turbine rotor blade 4 Turbine scroll 5 Turbine casing 6 Turbine back plate 8 Bearing stand 10 Oil supply hole 11 Oil supply hole for nozzle injection 12 Injection nozzle 12a Injection hole
Claims (1)
スタービン又はターボチャージャー等のターボ機械にお
いて、タービンロータ背面部に向けて軸受け潤滑油の一
部を噴射する噴射ノズルを設けてなることを特徴とする
タービンロータの冷却装置。1. A turbomachine, such as a radial flow gas turbine or a turbocharger, which uses a high-temperature high-pressure gas as a working fluid, is provided with an injection nozzle for injecting a part of the bearing lubricating oil toward the back surface of the turbine rotor. Characteristic turbine rotor cooling device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5484496A JPH09250353A (en) | 1996-03-12 | 1996-03-12 | Cooling device of turbine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5484496A JPH09250353A (en) | 1996-03-12 | 1996-03-12 | Cooling device of turbine rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH09250353A true JPH09250353A (en) | 1997-09-22 |
Family
ID=12981929
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP5484496A Pending JPH09250353A (en) | 1996-03-12 | 1996-03-12 | Cooling device of turbine rotor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH09250353A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002129969A (en) * | 2000-10-25 | 2002-05-09 | Nsk Ltd | Rotation supporting device for turbocharger |
| JP2002129968A (en) * | 2000-10-24 | 2002-05-09 | Nsk Ltd | Rotation supporting device for turbocharger |
| JP2002129967A (en) * | 2000-10-24 | 2002-05-09 | Nsk Ltd | Rotation supporting device for turbocharger |
| JP2009243306A (en) * | 2008-03-28 | 2009-10-22 | Ihi Corp | Supercharger and its cooling method |
| JP2013092086A (en) * | 2011-10-25 | 2013-05-16 | Ihi Corp | Turbocharger |
| CN105587347A (en) * | 2014-11-06 | 2016-05-18 | 通用电气公司 | Turbomachine including seal member and turbomachine system |
| KR101877119B1 (en) * | 2016-06-30 | 2018-07-10 | 현대위아 주식회사 | Turbo-charger |
| US10669891B2 (en) | 2015-08-11 | 2020-06-02 | Ihi Corporation | Bearing structure and turbocharger |
-
1996
- 1996-03-12 JP JP5484496A patent/JPH09250353A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002129968A (en) * | 2000-10-24 | 2002-05-09 | Nsk Ltd | Rotation supporting device for turbocharger |
| JP2002129967A (en) * | 2000-10-24 | 2002-05-09 | Nsk Ltd | Rotation supporting device for turbocharger |
| JP2002129969A (en) * | 2000-10-25 | 2002-05-09 | Nsk Ltd | Rotation supporting device for turbocharger |
| JP2009243306A (en) * | 2008-03-28 | 2009-10-22 | Ihi Corp | Supercharger and its cooling method |
| JP2013092086A (en) * | 2011-10-25 | 2013-05-16 | Ihi Corp | Turbocharger |
| CN105587347A (en) * | 2014-11-06 | 2016-05-18 | 通用电气公司 | Turbomachine including seal member and turbomachine system |
| US10669891B2 (en) | 2015-08-11 | 2020-06-02 | Ihi Corporation | Bearing structure and turbocharger |
| DE112016003647B4 (en) | 2015-08-11 | 2024-05-08 | Ihi Corporation | Bearing structure and turbocharger |
| KR101877119B1 (en) * | 2016-06-30 | 2018-07-10 | 현대위아 주식회사 | Turbo-charger |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20030930 |