JPH06213447A - Gas turbine burner and flame stabilizer thereof - Google Patents
Gas turbine burner and flame stabilizer thereofInfo
- Publication number
- JPH06213447A JPH06213447A JP5007794A JP779493A JPH06213447A JP H06213447 A JPH06213447 A JP H06213447A JP 5007794 A JP5007794 A JP 5007794A JP 779493 A JP779493 A JP 779493A JP H06213447 A JPH06213447 A JP H06213447A
- Authority
- JP
- Japan
- Prior art keywords
- gas turbine
- ring
- flame stabilizer
- turbine combustor
- section
- 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
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明はガスタービン燃焼器およ
び保炎器に係り、特に、保炎器を有するガスタービン燃
焼器に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine combustor and a flame stabilizer, and more particularly to a gas turbine combustor having a flame stabilizer.
【０００２】[0002]
【従来の技術】従来のガスタービン燃焼器を、図７〜１
３を用いて説明する。2. Description of the Related Art A conventional gas turbine combustor is shown in FIGS.
3 will be used for the explanation.
【０００３】図７、８及び図９は、それぞれガスタービ
ン燃焼器における初期燃焼、中間燃焼及び定常燃焼各状
態の説明図、図１０は従来の保炎器の構造と正常燃焼時
の火炎の状態の説明図、図１１は同じく火炎巻き込み時
の火炎の状態の説明図、図１２は従来の保炎器における
温度分布の説明図、図１３は従来の保炎器における熱応
力分布の説明図である。１０は燃料を示している。FIGS. 7, 8 and 9 are explanatory views of the states of initial combustion, intermediate combustion and steady combustion in the gas turbine combustor, respectively, and FIG. 10 is the structure of a conventional flame stabilizer and the state of flame during normal combustion. FIG. 11, FIG. 11 is an explanatory view of the state of the flame when the flame is involved, FIG. 12 is an explanatory view of temperature distribution in the conventional flame stabilizer, and FIG. 13 is an explanatory view of thermal stress distribution in the conventional flame stabilizer. is there. 10 has shown the fuel.
【０００４】ガスタービン燃焼器１は、圧縮機（図示せ
ず）から供給された高圧の空気１１を燃焼室内に導き、
１段目燃料ノズル７、補助バーナ燃料ノズル１４および
２段目燃料ノズル８より燃焼室に供給される燃料を燃焼
させている。The gas turbine combustor 1 introduces high pressure air 11 supplied from a compressor (not shown) into the combustion chamber,
The fuel supplied to the combustion chamber from the first stage fuel nozzle 7, the auxiliary burner fuel nozzle 14 and the second stage fuel nozzle 8 is burned.
【０００５】すなわち、ガスタービン燃焼器１は１段燃
焼気筒５と２段燃焼気筒６とを有しており、１段燃焼気
筒５には１段目燃料ノズル７および補助バーナ燃料ノズ
ル１４が、２段目燃焼気筒６には２段目燃料ノズル８
が、それぞれ設置されている。２段燃焼気筒６には２段
目燃料ノズル８の横には、空気流入口９があり、２段目
燃料ノズル８からの燃料１０と空気１１とが混じりあっ
て、２段目予混合気流１５となり、この混じりあう場所
を予混合器１２と呼んでいる。また、予混合器１２から
２段目予混合気流１５が流出直後の、２段目予混合気流
１５の流通路上に保炎器１３が設置されている。That is, the gas turbine combustor 1 has a first-stage combustion cylinder 5 and a second-stage combustion cylinder 6, and the first-stage combustion cylinder 5 includes a first-stage fuel nozzle 7 and an auxiliary burner fuel nozzle 14. The second-stage combustion cylinder 6 has a second-stage fuel nozzle 8
But each is installed. The second-stage combustion cylinder 6 has an air inlet 9 beside the second-stage fuel nozzle 8, and the fuel 10 and the air 11 from the second-stage fuel nozzle 8 are mixed with each other, so that the second-stage premixed air flow is generated. It becomes 15, and this mixing place is called a premixer 12. Further, the flame stabilizer 13 is installed on the flow passage of the second-stage premixed airflow 15 immediately after the second-stage premixed airflow 15 flows out from the premixer 12.
【０００６】以下、ガスタービン燃焼器１の作動につい
て説明する。まず、１段目燃料２と補助バーナ燃料３と
を１段目燃料ノズル７と補助バーナ燃料ノズル１４か
ら、それぞれ１段目燃焼室１６に投入され、点火されて
１段目燃焼火炎１８となって燃焼する。この状態でガス
タービンの運転が開始されるが、このときに形成される
火炎の状態を図７に示す。The operation of the gas turbine combustor 1 will be described below. First, the first stage fuel 2 and the auxiliary burner fuel 3 are introduced into the first stage combustion chamber 16 from the first stage fuel nozzle 7 and the auxiliary burner fuel nozzle 14, respectively, and ignited to form the first stage combustion flame 18. To burn. The operation of the gas turbine is started in this state, and the state of the flame formed at this time is shown in FIG.
【０００７】次に、ガスタービンが、ある負荷に到達し
た段階で２段目燃料４が２段目燃料ノズル８から予混合
器１２に供給され、予混合器１２に供給された２段目燃
料４は図示されていない空気源から同じく予混合器１２
に供給される空気と混合して２段目予混合気流１５とし
て、２段目燃焼室１７へ供給される。２段目燃焼室１７
へ供給された２段目予混合気流１５は１段目燃焼火炎１
８により着火され、２段目燃焼火炎２０となる。この場
合、保炎器１３を設置することにより、２段目予混合気
流１５の燃料濃度が薄くても、安定燃焼し、また、１段
目燃焼火炎１８が消火されても、２段目燃焼火炎２０だ
けの安定燃焼が得られる。このときに形成される火炎の
状態を図８に示す。Next, when the gas turbine reaches a certain load, the second-stage fuel 4 is supplied from the second-stage fuel nozzle 8 to the premixer 12, and the second-stage fuel supplied to the premixer 12 is supplied. 4 is also a premixer 12 from an air source (not shown)
Is supplied to the second-stage combustion chamber 17 as a second-stage premixed air flow 15 mixed with the air supplied to the second stage combustion chamber 17. Second stage combustion chamber 17
The second-stage premixed airflow 15 supplied to the first-stage combustion flame 1
It is ignited by 8 and becomes the second stage combustion flame 20. In this case, by installing the flame stabilizer 13, even if the fuel concentration of the second-stage premixed airflow 15 is low, stable combustion is achieved, and even if the first-stage combustion flame 18 is extinguished, the second-stage combustion flame 18 is combusted. Stable combustion of only the flame 20 is obtained. The state of the flame formed at this time is shown in FIG.
【０００８】続いて、補助バーナ燃料ノズル１４からの
補助バーナ燃料３の供給が停止され、補助バーナ燃料３
は１段目燃料２へ合流して１段目燃料ノズル７から供給
され、補助バーナ火炎１９は消火する。その後、１段目
燃焼火炎１８は渦流に流されて、１段目燃焼室１６の保
炎はなくなり、２段目燃焼火炎２０によって、火炎が保
たれている。この時に保たれている火炎の状態を図９に
示す。Subsequently, the supply of the auxiliary burner fuel 3 from the auxiliary burner fuel nozzle 14 is stopped, and the auxiliary burner fuel 3
Is joined to the first-stage fuel 2 and supplied from the first-stage fuel nozzle 7, and the auxiliary burner flame 19 is extinguished. After that, the first-stage combustion flame 18 is caused to flow in a vortex flow, the flame holding of the first-stage combustion chamber 16 disappears, and the flame is maintained by the second-stage combustion flame 20. The state of the flame maintained at this time is shown in FIG.
【０００９】このように、ガスタービン燃焼器１は３段
階の燃焼過程を有しているが、これらの燃焼過程におい
て、重要な役割を果たしているのが、保炎器１３であ
る。保炎器１３は、第２段階及び第３段階における燃焼
の安定性を確保し、Ｎox濃度を減少させる役目を有して
いる。As described above, the gas turbine combustor 1 has three stages of combustion processes, and the flame stabilizer 13 plays an important role in these combustion processes. The flame stabilizer 13 has the role of ensuring the stability of combustion in the second and third stages and reducing the Nox concentration.
【００１０】保炎器１３の構造と正常燃焼時の火炎の状
態を図１０に示す。保炎器１３は、２段目予混合気流１
５が予混合器１２から流出した直後の位置に設けてあ
り、図１０の場合は、予混合器１２の端部に固定されて
いる。保炎器１３は予混合器１２の出口部の可燃予混合
気流１５の流通路上に設置された円筒状台２３、肉厚が
増大する断面が台形状のリング状の円板２２とからな
り、円筒状台２３の端部に台形状断面を有するリング状
円板２２とを接続して構成されている。FIG. 10 shows the structure of the flame stabilizer 13 and the state of the flame during normal combustion. The flame stabilizer 13 is the second stage premixed air flow 1
5 is provided at a position immediately after flowing out from the premixer 12, and in the case of FIG. 10, it is fixed to the end portion of the premixer 12. The flame stabilizer 13 comprises a cylindrical base 23 installed on the flow path of the combustible premixed airflow 15 at the outlet of the premixer 12, and a ring-shaped disc 22 having a trapezoidal cross section with an increased wall thickness. It is configured by connecting a ring-shaped disc 22 having a trapezoidal cross section to an end of a cylindrical base 23.
【００１１】火炎は、正常燃焼時では、図１０に示すよ
うに、保炎器１３の台形状断面の底辺である端面２１側
のみ発生しており、火炎に接触するのは、端面２１のみ
である。台形状断面のリング状円板２２の斜辺部分２６
及び円筒状台２３の内外周面２７に接触しているのは、
２段目予混合気流１５である。この気流は燃焼していな
いために、圧縮空気１１の温度に近く、したがって、台
形状断面のリング状円板２２の斜辺部分２６及び円筒状
台２３の内外周面２７の温度は比較的低い状態にある。During normal combustion, the flame is generated only on the side of the end face 21 which is the base of the trapezoidal cross section of the flame stabilizer 13 as shown in FIG. 10, and only the end face 21 comes into contact with the flame. is there. The hypotenuse portion 26 of the ring-shaped disc 22 having a trapezoidal cross section
And, what is in contact with the inner and outer peripheral surface 27 of the cylindrical base 23 is
It is the second stage premixed air flow 15. Since this air flow is not combusted, it is close to the temperature of the compressed air 11, and therefore the temperature of the hypotenuse portion 26 of the ring-shaped disc 22 having a trapezoidal cross section and the inner and outer peripheral surfaces 27 of the cylindrical base 23 are relatively low. It is in.
【００１２】しかし、ガスタービン燃焼器１の稼働中、
常に図１０に示したような火炎状態にあるわけではな
く、火炎巻き込み現象が発生する。図１１は火炎巻き込
み時の火炎の状態を示す。すなわち、燃料の制御系統の
変動による火炎のゆらぎによって、台形状断面リング状
円板２２の斜辺部分２６を伝って、円筒状台２３にまで
火炎が巻き込まれる現象が頻発する。したがって、火炎
の状態は、正常燃焼時のものと火炎巻き込み時のものが
繰り返される。However, during operation of the gas turbine combustor 1,
The flame state is not always as shown in FIG. 10, and a flame entrainment phenomenon occurs. FIG. 11 shows the state of the flame when the flame is involved. That is, due to the fluctuation of the flame due to the fluctuation of the fuel control system, the phenomenon that the flame is caught up to the cylindrical base 23 along the hypotenuse portion 26 of the trapezoidal ring disk 22 frequently occurs. Therefore, the state of flame is repeated between the normal combustion and the flame entrainment.
【００１３】上記のことから、保炎器１３は、図１２に
示すような温度分布となる。図１２に記載された数値
は、保炎器１３の金属表面温度Ｔmetalと燃焼ガスの温
度Ｔgとの比率を示しており、図１２（a）は正常燃焼
時、図１２（b）は火炎巻き込み時の前記比率である。From the above, the flame stabilizer 13 has a temperature distribution as shown in FIG. The numerical values shown in FIG. 12 indicate the ratio between the metal surface temperature Tmetal of the flame stabilizer 13 and the temperature Tg of the combustion gas. FIG. 12 (a) shows the normal combustion, and FIG. 12 (b) shows the flame entrainment. It is the ratio of time.
【００１４】正常燃焼時には、保炎器１３の台形状断面
の底辺である端面２１に高温の火炎が、台形状断面のリ
ング状円板２２の斜辺部分２３及び円筒状台２３の内外
周面２７には低温の２段目予混合気流１５が、それぞれ
接触するため、端面２１が高温となり、台形状断面のリ
ング状円板２２の斜辺部分２６や円筒状台２３の内外周
面２７の温度は端面２１から離れるに伴い低くなる。斜
辺部分２６、内外周面２７の境界条件がほぼ対称である
ため、台形状断面のリング状円板２２や円筒状台２３の
等温線図は端面２１とほぼ平行となる。この温度分布に
より熱応力が発生する。この熱応力は２段目予混合気流
１５の着火、消火により繰り返えされ、場合によって
は、き裂が発生する恐れがある。At the time of normal combustion, a high temperature flame is generated on the end face 21 which is the bottom of the trapezoidal cross section of the flame stabilizer 13, and the oblique side portion 23 of the ring-shaped disc 22 having the trapezoidal cross section and the inner and outer peripheral surfaces 27 of the cylindrical base 23. Since the low-temperature second-stage premixed air currents 15 come into contact with each other, the end surface 21 becomes high in temperature, and the temperature of the hypotenuse portion 26 of the ring-shaped disc 22 having a trapezoidal cross section and the inner and outer peripheral surfaces 27 of the cylindrical base 23 is increased. It becomes lower as the distance from the end face 21 increases. Since the boundary conditions of the hypotenuse portion 26 and the inner and outer peripheral surfaces 27 are substantially symmetrical, the isotherms of the ring-shaped disc 22 and the cylindrical base 23 having a trapezoidal cross section are substantially parallel to the end surface 21. This temperature distribution causes thermal stress. This thermal stress is repeated due to ignition and extinction of the second-stage premixed air stream 15, and in some cases, a crack may occur.
【００１５】一方、燃料の制御系統の変動による火炎の
ゆらぎにより、台形状断面のリング状円板２２の斜辺部
分２６や円筒状台２３の内外周面２７にまで、火炎が巻
き込まれた場合は、低温の２段目予混合気流１５による
冷却効果が減少するため、端面２１や台形状断面リング
状円板２２の斜辺部分２６や円筒状台２３の内外周面２
７が高温になり、図１２（b）に示すような温度分布に
なる。その結果、この温度分布により熱応力が発生す
る。On the other hand, when the flame is entangled by the fluctuation of the flame due to the fluctuation of the fuel control system, the oblique side 26 of the ring-shaped disc 22 having a trapezoidal cross section and the inner and outer peripheral surfaces 27 of the cylindrical base 23 are caught. Since the cooling effect of the low-temperature second-stage premixed airflow 15 is reduced, the slanted portion 26 of the end face 21, the trapezoidal ring-shaped disc 22, and the inner and outer peripheral faces 2 of the cylindrical base 23.
7 becomes a high temperature and has a temperature distribution as shown in FIG. As a result, thermal stress is generated due to this temperature distribution.
【００１６】正常燃焼時に発生する熱応力と火炎巻き込
み時に発生する熱応力が、頻繁に繰り返される結果、疲
労損傷が生じ、高温状態であることにより金属材料の強
度も大幅に低下していることも影響して、寿命は大幅に
低下する。Frequent repetition of the thermal stress generated during normal combustion and the thermal stress generated during flame entrainment results in fatigue damage, and the strength of the metal material is significantly reduced due to high temperature. As a result, the life is greatly reduced.
【００１７】上記のように、熱応力及び繰返し熱応力に
より、保炎器１３にき裂が発生し、そのき裂が進展す
る。特に、繰返し熱応力は、火炎のゆらぎによる場合
が、２段目予混合気流１５の着火、消火による場合より
も頻繁であり、これがガスタービン燃焼器１の寿命に極
めて大きな影響を与えている。したがって、従来の燃焼
器は保炎器１３に損傷が生じ、損傷して脱落した保炎器
がタービンに損傷を与える可能性があり、信頼性に問題
があるとともに、頻繁な保炎器の交換が必要であった。As described above, due to the thermal stress and the repeated thermal stress, a crack is generated in the flame stabilizer 13, and the crack propagates. In particular, the cyclic thermal stress is more frequent in the case of flame fluctuation than in the case of igniting and extinguishing the second-stage premixed air stream 15, which has an extremely large effect on the life of the gas turbine combustor 1. Therefore, in the conventional combustor, the flame stabilizer 13 may be damaged, and the damaged and dropped flame stabilizer may damage the turbine, resulting in reliability problems and frequent flame stabilizer replacement. Was needed.
【００１８】[0018]
【発明が解決しようとする課題】ガスタービン燃焼器で
は、保炎器は低Ｎox化のために、不可欠なものとなって
いるが、従来の保炎器では、過大な熱応力が発生し、こ
れが、保炎器に重大な損傷を与えていた。In the gas turbine combustor, the flame stabilizer is indispensable for lowering Nox, but in the conventional flame stabilizer, excessive thermal stress is generated, This caused serious damage to the flame holder.
【００１９】本発明の目的は、保炎器の損傷をなくし、
ガスタービン燃焼器の信頼性を向上させることにある。The object of the present invention is to eliminate damage to the flame stabilizer,
It is to improve the reliability of the gas turbine combustor.
【００２０】[0020]
【課題を解決するための手段】上記の目的は、燃焼用の
燃料と空気とを混合して可燃予混合気体を作成する二重
円筒状の予混合器の環状の出口部の前記可燃予混合気体
の流通路上に、該予混合器と同心状に設置された円筒状
台と、該円筒状台の下流端に結合され、前記可燃予混合
気体の下流側に向かって、肉厚が増大する断面が台形状
のリング状の円板とを含んでなる保炎器を有するガスタ
ービン燃焼器において、前記台形状断面を有するリング
状円板と円筒状台に、若しくは、台形状断面を有するリ
ング状円板のみに、該リング状円板の台形状断面の底面
をなす下流側端面に開口し前記可燃予混合気体の流れ方
向上流側に向かって深さを持つ複数の切れ目を設けるこ
とにより達成される。SUMMARY OF THE INVENTION The above object is to provide the combustible premix at the annular outlet of a double cylindrical premixer for mixing combustible fuel and air to create a combustible premixed gas. A cylindrical base, which is installed concentrically with the premixer, is connected to the downstream end of the cylindrical base on the gas flow passage, and the wall thickness increases toward the downstream side of the combustible premixed gas. A gas turbine combustor having a flame stabilizer including a trapezoidal ring-shaped disc, wherein the ring-shaped disc having the trapezoidal section and the cylindrical stand, or the ring having the trapezoidal section. Achieved by providing only a circular disc with a plurality of cuts that are open to the downstream end face that forms the bottom of the trapezoidal cross section of the ring-shaped disc and that have a depth toward the upstream side in the flow direction of the combustible premixed gas. To be done.
【００２１】前記台形状断面のリング状円板と円筒状台
の内周及び外周部にフィンが設けられている場合は、該
フィンを切断して切れ目を形成すればよい。When fins are provided on the inner and outer peripheries of the ring-shaped disk having the trapezoidal cross section and the cylindrical base, the fins may be cut to form a cut.
【００２２】また、前記切れ目は、ガスタービン燃焼器
の軸線に対し放射状に形成されているのが好ましく、さ
らにリング状円板の周長を等間隔に分割するように配置
されていることが好ましい。The cuts are preferably formed radially with respect to the axis of the gas turbine combustor, and are preferably arranged so as to divide the circumference of the ring-shaped disc into equal intervals. .
【００２３】さらに前記切れ目が、リング状円板の台形
状断面の底面をなす下流側端面に開口し、その深さは当
該ガスタービン燃焼器の稼働時、前記台形状断面を有す
るリング状円板に発生する圧縮応力が該円板の前記底面
から上流側になるにつれて減少しゼロとなる位置に達す
る深さであることが好ましく、切れ目の幅をｂ、保炎器
材料の線膨張係数をα、室温とガスタービン運転時の保
炎器切れ目部分の温度との温度差をＴ0、保炎器の半径
をｒ、切れ目の数をＸとした時、次式の関係が成立して
いることが好ましい。Further, the cut is opened to the downstream end face which forms the bottom of the trapezoidal cross section of the ring-shaped disc, and the depth thereof is the ring-shaped disc having the trapezoidal cross section when the gas turbine combustor is in operation. It is preferable that the compressive stress generated in the disk is such that the compressive stress decreases from the bottom surface of the disc toward the upstream side and reaches a position where the compressive stress reaches zero, the cut width is b, and the linear expansion coefficient of the flame stabilizer material is α. , Where the temperature difference between the room temperature and the temperature of the flame stabilizer cut portion during gas turbine operation is T 0 , the radius of the flame stabilizer is r, and the number of cuts is X, the following relationship must be established. Is preferred.
【００２４】ｂ≧αＴ0・２πｒ／Ｘ さらにまた、切れ目の底部は、少なくとも直径がｂの円
弧で形成されているのが好ましい。B ≧ αT 0 · 2πr / X Furthermore, it is preferable that the bottom of the cut is formed as an arc having a diameter of at least b.
【００２５】[0025]
【作用】保炎器の円筒状台と断面が台形状のリング状円
板に複数個の切れ目を入れてあるので、切れ目を入れて
いない場合に発生する熱応力は、正常燃焼時、及び火炎
巻き込み時共に解放され、大きく低減される。したがっ
て、正常燃焼と火炎の巻き込みとの繰り返しにより発生
する繰り返し熱応力も大幅に低減され、疲労損傷の発生
が抑制されるので保炎器の信頼性が向上する。[Function] Since the flame holder has a cylindrical base and a ring-shaped disc having a trapezoidal cross section with a plurality of cuts, the thermal stress generated when the cuts are not made is generated during normal combustion and flame. It is released at the time of involvement and greatly reduced. Therefore, the repetitive thermal stress generated by the repetition of normal combustion and the entrainment of flame is significantly reduced, the occurrence of fatigue damage is suppressed, and the reliability of the flame stabilizer is improved.
【００２６】また、切れ目は保炎器において、熱応力が
発生しやすい箇所に設けてあるので、効率良く熱応力が
低減できる。また、保炎器の内周側、外周側の境界条件
は対称であるので、切れ目を入れても変形することな
く、正常に保炎性能が保たれる。Further, since the break is provided in the flame stabilizer at a location where thermal stress is likely to occur, the thermal stress can be efficiently reduced. Further, since the boundary conditions on the inner circumference side and the outer circumference side of the flame stabilizer are symmetrical, the flame holding performance is maintained normally without being deformed even if a break is made.
【００２７】更に、保炎器が膨張しても、切れ目が閉じ
る程度の幅を切れ目に設けてあるので、上記の熱応力の
低減が阻害されることはない。また、定常燃焼中は熱膨
張によって切れ目が完全に閉じているので、切れ目から
予混合気流が漏れることはなく、保炎性能は正常に保持
される。Further, even if the flame stabilizer expands, the width of the break is set so that the break is closed, so that the reduction of the thermal stress is not hindered. Further, since the cut is completely closed by thermal expansion during steady combustion, the premixed air flow does not leak from the cut, and the flame holding performance is normally maintained.
【００２８】[0028]
【実施例】以下、図面を参照して本発明の実施例を説明
する。Embodiments of the present invention will be described below with reference to the drawings.
【００２９】図１は、図７〜８に示すガスタービン燃焼
器１に本発明を適用した実施例における保炎器要部の模
式縦断面図、図２は図１のＡ方向矢視平面図、図３は図
１のＢ方向矢視側面図、図４は切れ目の数と応力比の関
係の説明図である。24は切れ目、25は円孔を示してお
り、そのほかは前出の符号である。FIG. 1 is a schematic vertical sectional view of a main part of a flame stabilizer in an embodiment in which the present invention is applied to the gas turbine combustor 1 shown in FIGS. 7 to 8, and FIG. 2 is a plan view in the direction of arrow A in FIG. 3, FIG. 3 is a side view as seen from the direction of arrow B in FIG. 1, and FIG. 4 is an explanatory diagram of the relationship between the number of cuts and the stress ratio. The numeral 24 indicates a break, the numeral 25 indicates a circular hole, and the other numerals are the same as those mentioned above.
【００３０】ガスタービン燃焼器１は先に述べたよう
に、１段燃焼気筒５と、１段燃焼気筒５の下流側外周に
１段燃焼気筒５と同心状に配置され、１段燃焼気筒５の
外周面との間に環状の予混合器１２を形成している２段
燃焼気筒６とを有しており、１段燃焼気筒５には１段目
燃料ノズル７および補助バーナ燃料ノズル１４が、２段
目燃焼気筒６には２段目燃料ノズル８が、それぞれ設置
されている。２段燃焼気筒６には、２段目燃料ノズル８
の横に空気流入口９が配置され、２段目燃料ノズル８か
らの燃料１０と空気流入口９からの空気１１とが混じり
あって、２段目予混合気流１５となり、この混じりあう
場所を予混合器１２と呼んでいる。また、予混合器１２
から２段目予混合気流１５が流出直後の、２段目予混合
気流１５の流通路上に保炎器１３が設置されている。As mentioned above, the gas turbine combustor 1 is arranged concentrically with the first-stage combustion cylinder 5 on the outer periphery of the first-stage combustion cylinder 5 on the downstream side of the first-stage combustion cylinder 5. The second stage combustion cylinder 6 forming an annular premixer 12 between the first stage combustion cylinder 5 and the first stage fuel nozzle 7 and the auxiliary burner fuel nozzle 14. Second-stage fuel nozzles 8 are installed in the second-stage combustion cylinders 6, respectively. The second-stage combustion cylinder 6 has a second-stage fuel nozzle 8
The air inflow port 9 is arranged next to, and the fuel 10 from the second-stage fuel nozzle 8 and the air 11 from the air inflow port 9 are mixed with each other to form the second-stage premixed airflow 15. It is called the premixer 12. Also, the premixer 12
The flame stabilizer 13 is installed on the flow passage of the second-stage premixed airflow 15 immediately after the outflow of the second-stage premixed airflow 15.
【００３１】図１はこの予混合器１２の下流端に配置さ
れた保炎器１３の断面を示している。予混合器１２は、
１段燃焼気筒５の軸線と同心状の外周円筒１２Ａ及び内
周円筒１２Ｂと、両円筒間に半径方向に放射状に配置さ
れて両者を結合している、軸線方向に伸びた平板状の複
数の連結材１２Ｃとを含んで形成されている。該連結材
１２Ｃの下流端２８は外周円筒１２Ａと内周円筒１２Ｂ
の下流側端部２９よりも上流側に位置している。保炎器
１３は、外周円筒１２Ａの内径と内周円筒１２Ｂの外径
のほぼ中間の径をなして内周円筒１２Ｂと同心状に配置
された円筒状台２３と、該円筒状台２３と同じ径を持ち
該円筒状台２３の下流端に結合された台形断面のリング
状円板２２とを含んで構成されている。円筒状台２３の
上流端は、前記連結材１２Ｃに形成された切り込み部に
嵌め込まれ、溶接により固着されている。FIG. 1 shows a cross section of the flame stabilizer 13 arranged at the downstream end of the premixer 12. The premixer 12 is
An outer peripheral cylinder 12A and an inner peripheral cylinder 12B that are concentric with the axis of the first-stage combustion cylinder 5, and a plurality of flat plate-shaped cylinders extending in the axial direction that are radially arranged between the cylinders and connect the two. The connecting material 12C is included. The downstream end 28 of the connecting member 12C has an outer peripheral cylinder 12A and an inner peripheral cylinder 12B.
Is located upstream of the downstream end portion 29 of the. The flame stabilizer 13 has a cylindrical base 23 arranged substantially concentrically with the inner peripheral cylinder 12B so as to have an inner diameter of the outer peripheral cylinder 12A and an outer diameter of the inner peripheral cylinder 12B, and the cylindrical base 23. And a ring-shaped disc 22 having a trapezoidal cross section and having the same diameter and connected to the downstream end of the cylindrical base 23. The upstream end of the cylindrical base 23 is fitted into the notch formed in the connecting member 12C and fixed by welding.
【００３２】本実施例では、保炎器１３の台形断面のリ
ング状円板（以下、リング状円板という）２２の周長が
等間隔に１６分割され、分割された各区域ごとに、リン
グ状円板２２に、半径方向に、保炎器１３の長手方向に
深さを持つ切れ目２４が入れられている。すなわち、切
れ目２４は燃焼器の軸線に対して放射状に配置されてお
り、リング状円板２２の内周面と外周面との間を貫通し
ている。なお、切れ目を入れたままでは、切れ目の先端
部の応力集中係数が大きくなり、割れ感受性に悪影響を
与えるために、この先端部には本実施例では、切れ目の
幅の３倍程度の直径を有する円孔２５が設けられ、切れ
目先端からのき裂の発生が防止されている。円孔２５の
直径は、少なくとも切れ目の幅とするのが望ましい。In the present embodiment, the circumference of a ring-shaped disk (hereinafter referred to as a ring-shaped disk) 22 having a trapezoidal cross section of the flame stabilizer 13 is divided into 16 equal intervals, and a ring is provided for each divided area. A cut 24 having a depth in the longitudinal direction of the flame stabilizer 13 is formed in the circular disc 22 in the radial direction. That is, the cuts 24 are arranged radially with respect to the axis of the combustor and penetrate between the inner peripheral surface and the outer peripheral surface of the ring-shaped disc 22. If the cut is left, the stress concentration coefficient at the tip of the cut becomes large, which adversely affects the susceptibility to cracking. Therefore, in this embodiment, the tip has a diameter of about three times the width of the cut. The circular hole 25 is provided to prevent the occurrence of cracks from the tip of the cut. The diameter of the circular hole 25 is preferably at least the width of the cut.
【００３３】本実施例では、上記のように、リング状円
板２２に１６個の切れ目を設けてあるが、切れ目の数を
多くするほど、つまり切れ目と切れ目の間隔を短くする
ほどリング状円板に発生する熱応力は低減する。切れ目
の数と熱応力の関係の一例を図４に示す。横軸は切れ目
の数、縦軸は任意の切れ目の数の時に発生する熱応力σ
と切れ目がないときに発生する熱応力σ0との比σ／σ0
を示している。切れ目は等間隔に設けてあるものとして
ある。図示した応力の比は、最大温度発生場所であると
同時に、最大応力発生場所でもあるリング状円板２２の
下流側端面２１の応力値の比を示している。この結果に
よれば、切れ目の数を無限に多くすれば、熱応力は無限
に小さくなるが、切れ目の数を無限に多くすることは現
実的ではない。したがって、切れ目を入れるに要する工
数、発生熱応力と許容応力との関係から、最適な切れ目
の数を選択すればよい。In this embodiment, as described above, the ring-shaped circular plate 22 is provided with 16 cuts. However, the larger the number of cuts, that is, the shorter the distance between the cuts, the ring-shaped circle. The thermal stress generated in the plate is reduced. FIG. 4 shows an example of the relationship between the number of cuts and thermal stress. The horizontal axis is the number of cuts, and the vertical axis is the thermal stress σ that occurs when the number of cuts is arbitrary.
And the thermal stress σ 0 that occurs when there is no break σ / σ 0
Is shown. The breaks are provided at equal intervals. The illustrated stress ratio indicates the ratio of the stress values of the downstream end face 21 of the ring-shaped disc 22 that is the maximum temperature generation location as well as the maximum stress generation location. According to this result, if the number of cuts is increased infinitely, the thermal stress will be decreased infinitely, but it is not realistic to increase the number of cuts infinitely. Therefore, the optimum number of breaks may be selected from the number of steps required to make a break and the relationship between the generated thermal stress and the allowable stress.
【００３４】本実施例では、切れ目２４は先に述べたよ
うに、ガスタービン燃焼器１の軸線に対し、放射状に配
置されているが、必ずしも放射状に配置されている必要
はなく、リング状円板２２の底面の周方向に沿った底面
の長さができるだけ平均して短くなるようになっていれ
ばよい。In the present embodiment, the cuts 24 are arranged radially with respect to the axis of the gas turbine combustor 1 as described above, but they are not necessarily arranged radially, and ring-shaped circles are not necessary. It is sufficient that the length of the bottom surface of the plate 22 along the circumferential direction is as short as possible on average.
【００３５】また、保炎器１３（細かくいうとリング状
円板２２）に入れる切れ目の軸線方向の長さ（端面２１
からの深さ）については、本来ならば、ある長さの切れ
目を入れた時の切れ目付け根近傍の発生熱応力を求め、
円孔などの応力集中を考慮しても、応力値が許容応力以
下である切れ目長さを採用すべきである。しかし、便宜
的には、次のようにして求めてもよい。本保炎器の構造
は燃焼器中心に対し対称であり、円筒状台２３およびリ
ング状円板２２の内周面と外周面の温度条件はほぼ等し
い。したがって、温度分布は保炎器の長手方向に差がつ
く傾向がある。その結果、発生熱応力は、図１３に示し
たように切れ目を設けていない保炎器の場合、端面２１
近傍では高温度のために圧縮応力であり、円筒状台２３
においては、比較的低温であるため、引張応力となり、
端面２１に平行な等応力線を有する応力分布となり、圧
縮応力から引張り応力まで連続的に分布している。した
がって、圧縮応力から引張応力に至る間に、必ず、応力
値がゼロになる位置がある。すなわち、圧縮熱応力が最
大値を示す端面２１から、この応力がゼロになる位置ま
で切れ目を入れればよい。Further, the length in the axial direction of the cut (the end face 21) to be inserted in the flame stabilizer 13 (ring-shaped disc 22 to be more precise).
For depth), the thermal stress generated near the base of the cut when a cut of a certain length is made is
Even considering stress concentration such as circular holes, the cut length whose stress value is less than the allowable stress should be adopted. However, for convenience, it may be obtained as follows. The structure of this flame stabilizer is symmetrical with respect to the center of the combustor, and the temperature conditions of the inner peripheral surface and the outer peripheral surface of the cylindrical base 23 and the ring-shaped circular plate 22 are substantially equal. Therefore, the temperature distribution tends to be different in the longitudinal direction of the flame stabilizer. As a result, in the case of the flame stabilizer having no cut as shown in FIG.
In the vicinity, there is compressive stress due to high temperature, and the cylindrical table 23
At, since it is a relatively low temperature, it becomes tensile stress,
The stress distribution has equal stress lines parallel to the end face 21, and is continuously distributed from compressive stress to tensile stress. Therefore, there is always a position where the stress value becomes zero between the compressive stress and the tensile stress. That is, a cut may be made from the end face 21 where the compressive thermal stress shows the maximum value to a position where this stress becomes zero.
【００３６】さらに、切れ目の幅は、次のようにして求
めた。すなわち、燃焼ガスに接触するリング状円板２２
は比較的高温であるので、熱膨張により切れ目が塞がれ
て、隣の部分と拘束しあうようであれば、切れ目が熱応
力の解放に寄与しなくなる。したがって、熱膨張して
も、切れ目が塞がれることのない切れ目の幅を次式によ
り決定した。Further, the width of the cut was determined as follows. That is, the ring-shaped disc 22 that contacts the combustion gas
Is relatively high in temperature, so if the cuts are closed due to thermal expansion and the adjacent parts are constrained, the cuts do not contribute to the release of thermal stress. Therefore, the width of the break which does not block the break even if it thermally expands was determined by the following equation.
【００３７】ｂ≧αＴ0・２πｒ／Ｘ ここで、ｂは切れ目の幅、αは保炎器材料の線膨張係
数、Ｔ0は室温と切れ目部分の燃焼時の温度との温度
差、ｒは保炎器の半径、Ｘは切れ目の数である。B ≧ αT 0 · 2πr / X where b is the width of the cut, α is the coefficient of linear expansion of the flame stabilizer material, T 0 is the temperature difference between room temperature and the combustion temperature of the cut, and r is The radius of the flame stabilizer, X is the number of cuts.
【００３８】図５、６は本発明の他の実施例を示す。図
５，６の実施例では、端面２１を冷却するために、図１
の実施例の円筒状台２３および台形断面のリング状円板
２２の内周面と外周面にフィン状の突起３０が設けられ
ている。突起３０を設けてあっても、切れ目２４は突起
３０を切断して設ければ、前記実施例と同様、リング状
円板２２の熱応力が低減される。5 and 6 show another embodiment of the present invention. In the embodiment shown in FIGS. 5 and 6, in order to cool the end face 21, as shown in FIG.
The fin-shaped protrusions 30 are provided on the inner and outer peripheral surfaces of the cylindrical base 23 and the ring-shaped disc 22 having a trapezoidal cross section in this embodiment. Even if the projection 30 is provided, if the cut 24 is provided by cutting the projection 30, the thermal stress of the ring-shaped disc 22 is reduced as in the above-described embodiment.
【００３９】[0039]
【発明の効果】本発明によれば、ガスタービン燃焼器
の、台形断面のリング状円板を用い、該台形断面の底面
に保炎させる保炎器において、該リング状円板の底面に
開口し、ガスタービン燃焼器の軸線方向に深さを持つ複
数の切れ目が形成されたので、ガスタービン燃焼器の正
常燃焼時と火炎の逆火時との繰返しによって、前記リン
グ状円板に発生する繰返し熱応力、起動、停止に伴って
発生する繰返し応力などが低減され、保炎器の損傷が防
止される。したがって、ガスタービン燃焼器の信頼性が
向上する。According to the present invention, in a flame stabilizer of a gas turbine combustor, which uses a ring-shaped disc having a trapezoidal cross section and holds flames on the bottom of the trapezoidal cross section, an opening is made at the bottom of the ring-shaped disc. However, since a plurality of cuts having a depth in the axial direction of the gas turbine combustor were formed, it is generated in the ring-shaped disc due to repetition of normal combustion of the gas turbine combustor and flame backfire. Repetitive thermal stress, repetitive stress generated by starting and stopping, etc. are reduced, and damage to the flame stabilizer is prevented. Therefore, the reliability of the gas turbine combustor is improved.
【図１】本発明の一実施例における保炎器要部の模式縦
断面図である。FIG. 1 is a schematic vertical sectional view of a main part of a flame stabilizer according to an embodiment of the present invention.
【図２】図１のＡ方向矢視平面図である。FIG. 2 is a plan view as seen in the direction of arrow A in FIG.
【図３】図１のＢ方向矢視平面図である。FIG. 3 is a plan view as seen from the direction of arrow B in FIG.
【図４】保炎器の切れ目の数と応力比との関係を示す概
念図である。FIG. 4 is a conceptual diagram showing the relationship between the number of cuts in the flame stabilizer and the stress ratio.
【図５】他の実施例における保炎器要部の模式縦断面図
である。FIG. 5 is a schematic vertical sectional view of a main part of a flame stabilizer according to another embodiment.
【図６】図５のＡ方向矢視平面図である。6 is a plan view as seen in the direction of arrow A in FIG.
【図７】ガスタービン燃焼器における初期燃焼状態の説
明図である。FIG. 7 is an explanatory diagram of an initial combustion state in the gas turbine combustor.
【図８】ガスタービン燃焼器における中間燃焼状態の説
明図である。FIG. 8 is an explanatory diagram of an intermediate combustion state in the gas turbine combustor.
【図９】ガスタービン燃焼器における定常燃焼状態の説
明図である。FIG. 9 is an explanatory diagram of a steady combustion state in the gas turbine combustor.
【図１０】従来の保炎器の構造と正常燃焼時の火炎の状
態を示すガスタービン燃焼器の部分断面図である。FIG. 10 is a partial cross-sectional view of a gas turbine combustor showing a structure of a conventional flame stabilizer and a state of a flame during normal combustion.
【図１１】従来の保炎器の火炎巻き込み時の火炎の状態
を示すガスタービン燃焼器の部分断面図である。FIG. 11 is a partial cross-sectional view of a gas turbine combustor showing a state of a flame when a conventional flame stabilizer is entrained by a flame.
【図１２】従来の保炎器における温度分布を示す概念図
である。FIG. 12 is a conceptual diagram showing a temperature distribution in a conventional flame stabilizer.
【図１３】従来の保炎器における熱応力分布を示す概念
図である。FIG. 13 is a conceptual diagram showing a thermal stress distribution in a conventional flame stabilizer.
１ ガスタービン燃焼器 ２ １段目燃料 ３ 補助バーナ燃料 ４ ２段目燃料 ５ １段燃焼気筒 ６ ２段燃焼気筒 ７ １段目燃料ノズル ８ ２段目燃料ノ
ズル ９ 空気流入口 １０ 燃料 １１ 空気 １２ 予混合器 １２Ａ 外周円筒 １２Ｂ 内周円筒 １２Ｃ 連結材 １３ 保炎器 １４ 捕助バーナ燃料ノズル １５ ２段目予混
合気流 １６ １段目燃焼室 １７ ２段目燃焼
室 １８ １段目燃焼火炎 １９ 補助バーナ
火炎 ２０ ２段目燃焼火炎 ２１ リング状円
板の下流側端面 ２２ 台形状断面のリング状円板 ２３ 円筒状台 ２４ 切れ目 ２５ 円孔 ２６ 台形状断面の斜辺部分 ２７ 円筒状台内
外周面 ２８ 連結材の下流側端部 ２９ 外周円筒，
内周円筒の下流側端部 ３０ 突起1 Gas Turbine Combustor 2 1st Stage Fuel 3 Auxiliary Burner Fuel 4 2nd Stage Fuel 5 1st Stage Combustion Cylinder 6 2nd Stage Combustion Cylinder 7 1st Stage Fuel Nozzle 8 2nd Stage Fuel Nozzle 9 Air Inlet 10 Fuel 11 Air 12 Premixer 12A Outer cylinder 12B Inner cylinder 12C Connecting material 13 Flame stabilizer 14 Auxiliary burner fuel nozzle 15 Second stage premixed air flow 16 1st stage combustion chamber 17 2nd stage combustion chamber 18 1st stage combustion flame 19 Auxiliary Burner flame 20 Second-stage combustion flame 21 Downstream end face of ring-shaped disc 22 Ring-shaped disc with trapezoidal cross section 23 Cylindrical platform 24 Cut 25 Circular hole 26 Oblique side portion of trapezoidal cross section 27 Cylindrical platform inner and outer peripheral surface 28 Downstream end of the connecting member 29 Peripheral cylinder,
Downstream end of inner cylinder 30 Protrusion
Claims (13)
混合気体を作成する二重円筒状の予混合器の環状の出口
部の前記可燃予混合気体の流通路上に、該予混合器と同
心状に設置された円筒状台と、該円筒状台の下流端に結
合され、前記可燃予混合気体の下流側に向かって、肉厚
が増大する断面が台形状のリング状の円板とを含んでな
る保炎器を有するガスタービン燃焼器において、前記台
形状断面を有するリング状円板と円筒状台に、若しく
は、台形状断面を有するリング状円板のみに、該リング
状円板の台形状断面の底面をなす下流側端面に開口し前
記可燃予混合気体の流れ方向上流側に向かって深さを持
つ複数の切れ目を有することを特徴とするガスタービン
燃焼器。1. A premixed combustible premixed gas flow passage at an annular outlet of a double cylindrical premixer for mixing combustible fuel and air to produce a combustible premixed gas. A cylindrical base that is installed concentrically with the container, and a ring-shaped circle that has a trapezoidal cross section that is connected to the downstream end of the cylindrical base and that increases in wall thickness toward the downstream side of the combustible premixed gas. In a gas turbine combustor having a flame stabilizer including a plate, the ring-shaped disc having the trapezoidal cross section and the cylindrical platform, or only the ring-shaped disc having the trapezoidal cross section, A gas turbine combustor having a plurality of cuts which are open at a downstream end face which forms a bottom surface of a trapezoidal cross section of a disc and which has a depth toward an upstream side in a flow direction of the combustible premixed gas.
台の内周及び外周部にフィンが設けられており、切れ目
は該フィンを切断して形成されていることを特徴とする
請求項１に記載のガスタービン燃焼器。2. A ring-shaped disc having a trapezoidal cross section and fins are provided on an inner circumference and an outer circumference of the cylindrical stand, and the cuts are formed by cutting the fins. The gas turbine combustor according to Item 1.
線に対し放射状に形成されていることを特徴とする請求
項１または２に記載のガスタービン燃焼器。3. The gas turbine combustor according to claim 1, wherein the cuts are formed radially with respect to an axis of the gas turbine combustor.
間隔に分割するように配置されていることを特徴とする
請求項１乃至３のいずれかに記載のガスタービン燃焼
器。4. The gas turbine combustor according to claim 1, wherein the cuts are arranged so as to divide the circumference of the ring-shaped disc into equal intervals.
面の底面をなす下流側端面に開口し、その深さは当該ガ
スタービン燃焼器の稼働時、前記台形状断面を有するリ
ング状円板に発生する圧縮応力が該円板の前記底面から
上流側になるにつれて減少しゼロとなる位置に達する深
さであることを特徴とする請求項１乃至４のいずれかに
記載のガスタービン燃焼器。5. The ring-shaped circle having the trapezoidal cross section opens at the downstream end face forming the bottom surface of the trapezoidal cross section of the ring-shaped disc, and the depth thereof is in operation during operation of the gas turbine combustor. 5. The gas turbine combustion according to claim 1, wherein the compressive stress generated in the plate has such a depth that the compressive stress decreases from the bottom surface of the disc toward the upstream side and reaches a position where the compressive stress reaches zero. vessel.
数をα、室温とガスタービン運転時の保炎器切れ目部分
の温度との温度差をＴ0、保炎器の半径をｒ、切れ目の
数をＸとした時、次式の関係が成立していることを特徴
とする請求項１乃至５のいずれかに記載のガスタービン
燃焼器。 ｂ≧αＴ0・２πｒ／Ｘ6. The width of the cut is b, the linear expansion coefficient of the flame stabilizer material is α, the temperature difference between room temperature and the temperature of the flame stabilizer cut portion during gas turbine operation is T 0 , and the radius of the flame stabilizer is The gas turbine combustor according to any one of claims 1 to 5, wherein the following relationship is established, where r and the number of cuts are X. b ≧ αT 0 · 2πr / X
れ、円筒状台から遠い側でかつ円筒状台の軸線に垂直な
端面を底面とする断面が台形状のリング状の円板とを含
んでなり、前記台形状の底面をなす部分を保炎面とす
る、ガスタービン燃焼器用保炎器において、前記台形状
断面を有するリング状円板と円筒状台に、若しくは、台
形状断面を有するリング状円板のみに、該リング状円板
の台形状断面の底面をなす下流側端面に開口し前記円筒
状台の軸線に沿って該円筒状台に向かう方向に深さを持
つ複数の切れ目を有することを特徴とするガスタービン
燃焼器用保炎器。7. A cylindrical base and a ring-shaped circle which is coupled to one end of the cylindrical base and has a trapezoidal cross section whose bottom face is an end face that is far from the cylindrical base and is perpendicular to the axis of the cylindrical base. In a flame stabilizer for a gas turbine combustor, which comprises a plate and has a portion forming the trapezoidal bottom surface as a flame-holding surface, a ring-shaped disc having the trapezoidal cross section and a cylindrical platform, or a platform. Only in a ring-shaped disc having a shaped cross section, a depth is formed in the direction toward the cylindrical base along the axis of the cylindrical base, which is opened at the downstream end face forming the bottom of the trapezoidal cross section of the ring-shaped disc. A flame stabilizer for a gas turbine combustor, which has a plurality of cuts.
台の内周及び外周部にフィンが設けられており、切れ目
は該フィンを切断して形成されていることを特徴とする
請求項７に記載のガスタービン燃焼器用保炎器。8. The ring-shaped disc having a trapezoidal cross section and fins are provided on the inner and outer peripheries of the cylindrical base, and the cuts are formed by cutting the fins. Item 7. A flame stabilizer for a gas turbine combustor according to Item 7.
射状に形成されていることを特徴とする請求項７または
８に記載のガスタービン燃焼器。9. The gas turbine combustor according to claim 7, wherein the cuts are formed radially with respect to the axis of the cylindrical base.
等間隔に分割するように配置されていることを特徴とす
る請求項７乃至９のいずれかに記載のガスタービン燃焼
器用保炎器。10. The flame stabilizer for a gas turbine combustor according to claim 7, wherein the cuts are arranged so as to divide the circumference of the ring-shaped disc into equal intervals. vessel.
断面の底面をなす端面に開口し、その深さは当該ガスタ
ービン燃焼器の稼働時、前記台形状断面を有するリング
状円板に発生する圧縮応力が該円板の前記底面から円筒
状台側になるにつれて減少しゼロとなる位置に達する深
さであることを特徴とする請求項７乃至１０のいずれか
に記載のガスタービン燃焼器用保炎器。11. The ring-shaped disc has an opening at an end face forming a bottom surface of the trapezoidal cross section of the ring-shaped disc, and the depth thereof is a ring-shaped disc having the trapezoidal cross-section when the gas turbine combustor is in operation. The gas turbine combustion according to any one of claims 7 to 10, wherein the compressive stress generated has a depth that decreases from the bottom surface of the disk toward the cylindrical base and reaches a position where the compression stress becomes zero. Veterinary flame stabilizer.
係数をα、室温とガスタービン運転時の保炎器切れ目部
分の温度との温度差をＴ0、保炎器の半径をｒ、切れ目
の数をＸとした時、次式の関係が成立していることを特
徴とする請求項７乃至１１のいずれかに記載のガスター
ビン燃焼器用保炎器。 ｂ≧αＴ0・２πｒ／Ｘ12. The width of the cut, b, the coefficient of linear expansion of the flame stabilizer material, α, the temperature difference between the room temperature and the temperature of the break of the flame stabilizer during gas turbine operation, T 0 , and the radius of the flame stabilizer. The flame stabilizer for a gas turbine combustor according to any one of claims 7 to 11, wherein the following relationship is established when r and the number of cuts are X. b ≧ αT 0 · 2πr / X
底部に、切れ目の長手方向に沿って少なくとも直径がｂ
の円弧が形成されていることを特徴とする請求項７乃至
１２のいずれかに記載のガスタービン燃焼器用保炎器。13. When the width of the cut is b, at least the diameter b is provided at the bottom of the cut along the longitudinal direction of the cut.
13. The flame stabilizer for a gas turbine combustor according to claim 7, wherein the arc is formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5007794A JPH06213447A (en) | 1993-01-20 | 1993-01-20 | Gas turbine burner and flame stabilizer thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5007794A JPH06213447A (en) | 1993-01-20 | 1993-01-20 | Gas turbine burner and flame stabilizer thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH06213447A true JPH06213447A (en) | 1994-08-02 |
Family
ID=11675561
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP5007794A Pending JPH06213447A (en) | 1993-01-20 | 1993-01-20 | Gas turbine burner and flame stabilizer thereof |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH06213447A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4814475A (en) * | 1987-09-28 | 1989-03-21 | Toshiba Silicone Co., Ltd. | Vinyl silane compounds |
| US10107501B2 (en) | 2013-03-21 | 2018-10-23 | Mitsubishi Heavy Industries, Ltd. | Combustor and gas turbine |
-
1993
- 1993-01-20 JP JP5007794A patent/JPH06213447A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4814475A (en) * | 1987-09-28 | 1989-03-21 | Toshiba Silicone Co., Ltd. | Vinyl silane compounds |
| US10107501B2 (en) | 2013-03-21 | 2018-10-23 | Mitsubishi Heavy Industries, Ltd. | Combustor and gas turbine |
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