JPS58222922A - Gas turbine device - Google Patents
Gas turbine deviceInfo
- Publication number
- JPS58222922A JPS58222922A JP10737882A JP10737882A JPS58222922A JP S58222922 A JPS58222922 A JP S58222922A JP 10737882 A JP10737882 A JP 10737882A JP 10737882 A JP10737882 A JP 10737882A JP S58222922 A JPS58222922 A JP S58222922A
- Authority
- JP
- Japan
- Prior art keywords
- gas turbine
- combustion
- switching valve
- feeding means
- air
- 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.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Regulation And Control Of Combustion (AREA)
- Supercharger (AREA)
Abstract
Description
【発明の詳細な説明】
本発明はガスタービン装置に関し、特にガスタービンと
空気圧送手段とを同軸に連結し、燃焼手段力・ら発生す
る燃焼排ガスによってガスタービンを駆動するとともに
空気圧送手段を駆動して前記燃焼手段に燃焼用突気を圧
送するようにしたガスタービン装置に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a gas turbine device, and particularly relates to a gas turbine device in which a gas turbine and an air pressure feeding means are coaxially connected, and the combustion exhaust gas generated from the combustion means drives the gas turbine and the air pressure feeding means. The present invention relates to a gas turbine device in which a combustion blast is force-fed to the combustion means.
第１図を参照して典型的な先行技術を説明する。A typical prior art technique will be described with reference to FIG.
発電機ｌを駆動するためのガスタービン２に、破線３で
示すように供給される燃料を燃焼手段４で燃焼すること
によって発生した燃焼排ガスが供給され、ガスタービン
２に同軸に連結されたコンプレツ・す５によって燃焼用
空気が燃焼手段４に供給きれる。このようなガスタービ
ン装置において、起動時においては、コンプレッサ５が
駆動されないので、コンプレッサ５による燃焼用空気の
併給を行なうだめに、電動モータ６を設け、ガスタービ
ン２の自刃運転が可能になるまで、電動モータ６により
コンプレッサ５およびガスタービン２を駆動している。A gas turbine 2 for driving a generator 1 is supplied with combustion exhaust gas generated by burning the supplied fuel in a combustion means 4 as shown by a broken line 3, and is connected coaxially to the gas turbine 2. - Combustion air can be completely supplied to the combustion means 4 through the suction 5. In such a gas turbine device, since the compressor 5 is not driven at startup, an electric motor 6 is provided in order for the compressor 5 to co-supply combustion air, and the electric motor 6 is installed until the gas turbine 2 can operate on its own. , a compressor 5 and a gas turbine 2 are driven by an electric motor 6.
この先行技術では、起動時のみに用いられる電動モータ
６が必要であり、しかも電動モータ６およびガスタービ
ン２を連動きせるためにガスタービン２の構造が複雑と
なる。This prior art requires an electric motor 6 that is used only during startup, and moreover, the structure of the gas turbine 2 becomes complicated because the electric motor 6 and the gas turbine 2 are operated together.
第２図を参照して、他の先行技術では起動時における燃
焼用空気を供給するためのプロア７を設けている。′１
−なわち（１）換弁８を備えコンプレッサ５および燃焼
手段４を連結する連結管９の途中における切換弁８の下
流側に、ブロア７の吐出口が切換弁１０を介して連結δ
れる。捷た連結管９における切換弁８の上線、側には、
開閉弁１１を備える放出管１２が連結きれる。この先行
技術では、起動時に９Ｊ換弁１０および開閉弁１１を開
弁し、切換弁８を閉弁する。その状恵でプロ７７を駆動
して燃焼用空気を燃焼手段４に供給し、ガスタービン２
が定常安定領域である高回転に運してから切換弁１０お
よび開閉弁１１を閉弁し、切換弁８を開弁する。したが
ってブロア７は高圧、高風祉であることが必要であり、
しかもガスタービン２が定常安定領域に達するまでにコ
ンプレッサ５から吐出される空気は放出管１２から無駄
に放出される。Referring to FIG. 2, in another prior art, a proar 7 is provided for supplying combustion air during startup. '1
- That is, (1) the discharge port of the blower 7 is connected via the switching valve 10 to the downstream side of the switching valve 8 in the middle of the connecting pipe 9 which has the switching valve 8 and connects the compressor 5 and the combustion means 4;
It will be done. On the upper line and side of the switching valve 8 in the disconnected connecting pipe 9,
The discharge pipe 12 equipped with the on-off valve 11 is now connected. In this prior art, at startup, the 9J switching valve 10 and the on-off valve 11 are opened, and the switching valve 8 is closed. In this situation, the pro 77 is driven to supply combustion air to the combustion means 4, and the gas turbine 2
After the rotation speed reaches a high speed in a steady stable region, the switching valve 10 and the on-off valve 11 are closed, and the switching valve 8 is opened. Therefore, the blower 7 needs to have high pressure and high wind power.
Moreover, the air discharged from the compressor 5 is wastefully discharged from the discharge pipe 12 until the gas turbine 2 reaches the steady-state stable region.
なお、第２図の先行技術において、ブロア７の、 容量
を小形化するためには、ガスタービン２が不安定な低速
回転時に（；ｌＪ換弁８，１０を切換えて自刃運転に移
行しなければならず、圧力や風量バランスの制御が困難
である１）
本発明は、上述の技術的課題を解決し、比較的小容量の
空気圧送手段により、容易に起動δせうるようにしたガ
スタービン装置を提供することを目的とする。In the prior art shown in Fig. 2, in order to reduce the capacity of the blower 7, it is necessary to switch the switching valves 8 and 10 to self-blade operation when the gas turbine 2 rotates at an unstable low speed. 1) The present invention solves the above-mentioned technical problems and provides a gas turbine device that can be easily started using a relatively small capacity air pressure feeding means. The purpose is to provide
以下、図面によって本発明の詳細な説明する。Hereinafter, the present invention will be explained in detail with reference to the drawings.
第３図は本発明の一実施例の系統図である。燃焼手段１
５には破線１６で示すように燃料が供給され、その燃料
の燃焼排ガスによってガスタービン１７が回転部ｕＪヒ
れる。ガスタービン１７によって発゛屯楓１８が駆動さ
れ、それによって電力が得られる。またガスタービン１
７には遠心コンプレッサや遠心ブロアなどのを気圧送手
段１９が同軸に連結されており、この空気圧送手段１９
によって燃焼手ｙｊ、１５に燃焼用叩気が供給きれる。FIG. 3 is a system diagram of one embodiment of the present invention. Combustion means 1
5 is supplied with fuel as shown by a broken line 16, and the gas turbine 17 is heated by the combustion exhaust gas of the fuel. The gas turbine 17 drives the generator 18, thereby obtaining electric power. Also gas turbine 1
7 is coaxially connected with air pressure feeding means 19 such as a centrifugal compressor or centrifugal blower.
As a result, the combustion air can be completely supplied to the combustion hand yj, 15.
空気圧送手段１９の吐出口は第１切換弁２０を＜ｒｉＰ
ｔ；６３！ＡＷｊ＊ ２１ ｅ（）Ｌ、”ＣＰａｍ＋Ｐ
１５ ｋｃＮＭ Ｇ ｌｉ’。The discharge port of the air pressure feeding means 19 connects the first switching valve 20 with <riP
t;63! AWj* 21 e()L,”CPam+P
15 kcNM G li'.
れる。この連結管２１における第１切換弁２０の上流側
および下流側を連結してバイパス管２２が設けられる。It will be done. A bypass pipe 22 is provided to connect the upstream and downstream sides of the first switching valve 20 in the connecting pipe 21 .
このバイパス管２２には、上流側力ら順に第２切換弁２
３、起動用ファン２４および第３切換弁２５が備えられ
る。なお、起動用ファン２４にはモータ２６が設けられ
る。This bypass pipe 22 has second switching valves 2 in order from the upstream side.
3. A starting fan 24 and a third switching valve 25 are provided. Note that the starting fan 24 is provided with a motor 26 .
このようなガスタービン装置において、起動特番こけ第
１切換弁２０を閉弁し、かつ第２および第３切換弁２３
．２５を開弁した状窓で、起動用ファン２４を駆動する
。起動用ファン２４によって吸引される空気は、空気圧
送手段１９をわずかに回転σせながら燃焼手段１５に供
給きれる。ここで燃焼手段１５に燃料を供給して、着火
、燃焼きせることにより発生した燃焼排ガスはガスター
ビン１７に送り込捷れる。それによってガスタービン１
７が回転駆動させるとともに、′：！ｆ！気圧送手段１
９が回転され、圧縮された空気が起動用ファン２４を介
して燃焼手段１５に四給びれる。このようにしてガスタ
ービン１７０回転数が次第に増加していく。ガスタービ
ン１７の回転数が充分に安定して自刃運転ができる程度
の高い値に達したときに、第２および第３切換弁２３．
２５を閉弁し、かつ％ＩＶＪ換弁２０を開弁する。そう
すれば、至気圧送手段１９から充分な量の空気が供給さ
れるので、安定した自刃運転に移行することができる。In such a gas turbine device, the first switching valve 20 is closed and the second and third switching valves 23 are closed.
．． With the window 25 open, the starting fan 24 is driven. The air sucked by the starting fan 24 can be completely supplied to the combustion means 15 while slightly rotating the air pressure feeding means 19. Here, fuel is supplied to the combustion means 15, and the combustion exhaust gas generated by ignition and combustion is sent to the gas turbine 17 and is shunted. Thereby gas turbine 1
7 drives the rotation and ′:! f! Air pressure feeding means 1
9 is rotated, and compressed air is supplied to the combustion means 15 via the starting fan 24. In this way, the rotation speed of the gas turbine 170 gradually increases. When the rotational speed of the gas turbine 17 is sufficiently stable and reaches a high enough value to allow self-cutting operation, the second and third switching valves 23.
25 is closed, and the %IVJ exchange valve 20 is opened. In this way, a sufficient amount of air is supplied from the maximum pressure feeding means 19, so that stable self-blade operation can be performed.
なお、起動用ファン２４は、燃焼手段１５で着火時に安
定した燃焼ゲ持続しうる程度の比較的小量の空気を供給
する小容量であればよい、、ただし、空気圧送手段１９
からの圧ｉｋＩ！空気が尋人されるので、若干の耐圧性
を有した起動用ファン２４であることが望ましい。Note that the starting fan 24 may have a small capacity that supplies a relatively small amount of air to the extent that stable combustion can be maintained during ignition in the combustion means 15; however, the air pressure feeding means 19
Pressure from ikI! Since the air is evacuated, it is desirable that the startup fan 24 has some pressure resistance.
本件発明者の行なった実験によれば、ガスタービン１７
の自刃運転が可能な燃焼手段１５の入口圧は２００ ｍ
ｍＡｑ 、 その風量は２ Ｎ ｒｒＰ／ｍ ｉ ｎ
、、モータ２６の助力は０．３ｋＷだけ少なくとも必要
であった。これに比べて、第２図に示された先行技術で
は、ガスタービン２を自刃運転するには、燃焼手段４の
入口圧は５００ ｍｍＡｑ、ブロア７の風量は２Ｎ ｒ
ｒ？／ ｍ ｉ ｎ、、そのブロア７の動力は１．５ｋ
Ｗだけ少なくとも必要であった。このことから本発明に
よれば、起動用ファン２４の吐田圧および助力を低減す
ることができることが明らかである。According to the experiments conducted by the inventor, the gas turbine 17
The inlet pressure of the combustion means 15 capable of self-operation is 200 m
mAq, its air volume is 2 N rrP/min
, the assistance of the motor 26 was required at least by 0.3 kW. In contrast, in the prior art shown in FIG. 2, in order for the gas turbine 2 to operate on its own, the inlet pressure of the combustion means 4 must be 500 mmAq, and the air volume of the blower 7 must be 2N r.
r? / min,, the power of the blower 7 is 1.5k
At least W was required. From this, it is clear that according to the present invention, the discharge pressure and assisting force of the startup fan 24 can be reduced.
第４図は本発明の他の実施例を示す。この実施例では、
空気圧送手段１９の上流側の管路２７に起動用ファン２
８を設け、かつ管路２９に開閉弁３０を設ける。起動時
には、開閉弁３０を閉じた１１で大気が起動用ファン２
８によって１吸引され、空気圧送手段１９をいわばす通
すして超過し、燃焼手段１５に送り込まれる。ガスター
ビン１７の自刃運転が可能となった後には、開閉弁３０
を開いたままにする。そのため２．２気圧送手段１９に
は開閉弁３０から管路２９を介して空気が吸引纒れる。FIG. 4 shows another embodiment of the invention. In this example,
A starting fan 2 is installed in the conduit 27 on the upstream side of the air pressure feeding means 19.
8 is provided, and an on-off valve 30 is provided in the conduit 29. At startup, when the on-off valve 30 is closed 11, the atmosphere flows into the startup fan 2.
1 is sucked in by 8, the air passes through the pneumatic feeding means 19 as it were, and is fed into the combustion means 15. After self-operation of the gas turbine 17 becomes possible, the on-off valve 30
Leave open. Therefore, air is sucked into the 2.2-atmosphere feeding means 19 from the on-off valve 30 through the conduit 29.
本発明の他の実施例として、第３切換弁２５を省略して
もよい。また、第２切換弁２３をる略し、第３切換弁２
、特許請求の範囲で言う第２ｖ′Ｊ換弁としてもよい。In other embodiments of the present invention, the third switching valve 25 may be omitted. In addition, the second switching valve 23 is abbreviated as the third switching valve 2.
, it may also be referred to as the 2nd v'J exchange valve in the claims.
上述のごとく本発明によれば、比較的小容量の起動用フ
ァンを設けた簡単な構成により、ガスタービンを安定し
て起動することが可能となる。As described above, according to the present invention, it is possible to stably start a gas turbine with a simple configuration including a relatively small-capacity starting fan.
第１図および第２図は先行技術をそれぞれ示す系統図、
第３図は本発明の一実施例の系統図、第４図は本発明の
他の実施例の系統図である３゜１５・・・燃焼手段、１
７・・・ガスタービン１． ｌ ９・・・空気圧送手段
、２０・・・第１１１７Ｊ換弁、２１・・・連結管、２
２・・・バイパス管、２３・・・第２切換弁、２４，２
８・・・起動用ファン、２５・・・％３切換弁、２６・
・・モータ
代理人 弁理士 西教圭一部
第１図
第２図
第３図
手続補正書
特許庁長官 殿
１、事件の表示
特願昭５７−１０７８７８
２、発明の名称
ガスタービン装置
３、補正をする者
事件との関係 出願人
住所
名称 （０２８） 大阪瓦斯株式会社代表者
４、代理人
住所 大阪市西区西本町１丁目１３番３８号 新興量ビ
ル明ｗＩ書の特許請求の範囲の欄
７、補正の内容
特許請求の範囲は別紙のとおり。
以上
特許請求の範囲
ｆｌ）ガスタービンと空気圧送手段とを同軸に連結し、
燃焼手段から発生する燃焼排ガスによってガスタービン
を駆動するとともに空気圧送手段を駆動して前記燃焼手
段に燃焼用空気を圧送するようにしたガスホービン装置
において、
前記空気圧送手段の出口と燃焼手段とけ途中に第１切換
弁を備える連結管で連結され、その連結管における第１
切換弁の上流側と下流側とを連結してバイパス管が設け
られ、前記バイパス管には上流側から順に第２切換弁お
よび起動用ファンが備えられることを特徴とするガスタ
ービン装置。
１１２Figures 1 and 2 are system diagrams showing the prior art, respectively;
Fig. 3 is a system diagram of one embodiment of the present invention, and Fig. 4 is a system diagram of another embodiment of the invention.
7... Gas turbine 1. l 9...Air pressure feeding means, 20...1117J exchange valve, 21...Connecting pipe, 2
2... Bypass pipe, 23... Second switching valve, 24, 2
8...Starting fan, 25...%3 switching valve, 26.
... Motor agent Patent attorney Kei Nishi Part 1 Figure 2 Figure 3 Procedural amendments Commissioner of the Japan Patent Office 1. Indication of the case Patent application 1987-107878 2. Name of the invention Gas turbine device 3. Amendment Relationship with the case filed by the applicant Applicant address name (028) Osaka Gas Co., Ltd. Representative 4, Agent address 1-13-38 Nishihonmachi, Nishi-ku, Osaka City Shinko Quantity Building Mei WI Document Scope of Claims Column 7, The content of the amendment and the scope of the claims are as shown in the attached sheet. Claims fl) The gas turbine and the air pressure feeding means are coaxially connected,
In a gas hobin device, in which a gas turbine is driven by the combustion exhaust gas generated from the combustion means, and an air pressure feeding means is driven to forcefully feed combustion air to the combustion means, there is provided a gas turbine between the outlet of the air pressure feeding means and the combustion means. connected by a connecting pipe provided with a first switching valve, and the first switching valve in the connecting pipe
A gas turbine apparatus characterized in that a bypass pipe is provided connecting an upstream side and a downstream side of a switching valve, and the bypass pipe is equipped with a second switching valve and a starting fan in order from the upstream side. 112
Claims (1)
段から発生する燃焼排ガスによってガスタービンを駆動
するとともに空気圧送手段を駆動して前記燃焼手段に燃
焼用空気を圧送するようにしたガスタービン装置におい
て、 前記突気圧送手段の出口と燃焼手段とは途中に第１切換
弁を備える連結管で連結され、その連結管における第１
ｆｊ′Ｊ換弁の上流側と下流側とを連結してバイパス管
が設けられ、前記バイパス管には上流側から順に第２ｔ
７１換弁および起動用ファンが備えられることを特徴と
するガスタービン装置。[Scope of Claims] A gas turbine and an air pressure feeding means are coaxially connected, and the gas turbine is driven by combustion exhaust gas generated from the combustion means, and the air pressure feeding means is driven to forcefully feed combustion air to the combustion means. In the gas turbine apparatus, the outlet of the sudden pressure feeding means and the combustion means are connected by a connecting pipe having a first switching valve in the middle, and the first switching valve in the connecting pipe is connected to the combustion means.
A bypass pipe is provided connecting the upstream side and the downstream side of the fj'J exchange valve, and the bypass pipe has a second t.
71 A gas turbine apparatus characterized in that it is equipped with a switching valve and a starting fan.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10737882A JPS58222922A (en) | 1982-06-21 | 1982-06-21 | Gas turbine device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10737882A JPS58222922A (en) | 1982-06-21 | 1982-06-21 | Gas turbine device |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP7854690A Division JPH02283824A (en) | 1990-03-26 | 1990-03-26 | Gas turbine device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS58222922A true JPS58222922A (en) | 1983-12-24 |
| JPH0313407B2 JPH0313407B2 (en) | 1991-02-22 |
Family
ID=14457588
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP10737882A Granted JPS58222922A (en) | 1982-06-21 | 1982-06-21 | Gas turbine device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS58222922A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5160069A (en) * | 1989-09-21 | 1992-11-03 | Allied-Signal Inc. | Integrated power unit combustion apparatus and method |
| US5235812A (en) * | 1989-09-21 | 1993-08-17 | Allied-Signal Inc. | Integrated power unit |
-
1982
- 1982-06-21 JP JP10737882A patent/JPS58222922A/en active Granted
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5160069A (en) * | 1989-09-21 | 1992-11-03 | Allied-Signal Inc. | Integrated power unit combustion apparatus and method |
| US5235812A (en) * | 1989-09-21 | 1993-08-17 | Allied-Signal Inc. | Integrated power unit |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0313407B2 (en) | 1991-02-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104755723B (en) | Power generation system | |
| JP4991986B2 (en) | Pressure incinerator equipment and its startup method | |
| KR20150041129A (en) | Hull resistance reduction system and hull resistance reduction method | |
| US4685287A (en) | Compressor system and start-up method therefor | |
| JPS58222922A (en) | Gas turbine device | |
| JPH0261392A (en) | Starting of turbocompressor and starting device | |
| JPH11229898A (en) | Start-up control device of gas turbine | |
| JPH02283824A (en) | Gas turbine device | |
| JP2003166428A (en) | Gas turbine generator and gas fuel booster applied thereto | |
| JP3137136B2 (en) | Turbine operation method for fuel cell power plant | |
| JPS6179856A (en) | Method of starting turbo-compressor | |
| CN206319961U (en) | LNG gas turbines and its activation system | |
| JP2004037038A (en) | Method and device for treating organic component-containing air and organic component-containing waste liquid | |
| JP3038986B2 (en) | Packaged gas turbine and method for purging exhaust system thereof and apparatus therefor | |
| JP4288845B2 (en) | Gas turbine system | |
| JPH0935735A (en) | Fuel cell power generation starting device | |
| WO2018119920A1 (en) | Lng gas turbine and starting system thereof | |
| JP6276880B2 (en) | Power generation system | |
| JPH0217697B2 (en) | ||
| JPH09166291A (en) | Storage equipment for low temperature liquefied gas | |
| JPS60160579A (en) | Starting of fuel cell power generation system | |
| JPS60160580A (en) | Starting of fuel cell power generation system | |
| JPH0217696B2 (en) | ||
| JP2000087760A (en) | Gas turbine output enhancement unit | |
| JPH10159575A (en) | Operating method for full fired heat recovery combined cycle system |