JP4240759B2 - Combustor tail cooling structure - Google Patents

Combustor tail cooling structure Download PDF

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Publication number
JP4240759B2
JP4240759B2 JP2000152426A JP2000152426A JP4240759B2 JP 4240759 B2 JP4240759 B2 JP 4240759B2 JP 2000152426 A JP2000152426 A JP 2000152426A JP 2000152426 A JP2000152426 A JP 2000152426A JP 4240759 B2 JP4240759 B2 JP 4240759B2
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Prior art keywords
cooling
tail
outlet
cooling medium
flange
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JP2001329858A (en
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武彦 清水
哲 羽田
弘一 赤城
克則 田中
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Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
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Priority to JP2000152426A priority Critical patent/JP4240759B2/en
Priority to DE60137099T priority patent/DE60137099D1/en
Priority to EP01108310A priority patent/EP1146289B1/en
Priority to CA002344012A priority patent/CA2344012C/en
Priority to US09/832,937 priority patent/US6553766B2/en
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Description

【０００１】
【発明の属する技術分野】
本発明は、ガスタービン用の燃焼器尾筒の冷却構造に関するものである。
【０００２】
【従来の技術】
近年、ガスタービン燃焼器として、例えば１５００℃級のガスタービンでも低ＮＯXが実現可能な、蒸気冷却式燃焼器が注目を集めている。即ち、燃焼器壁面を蒸気で冷却することにより、それまで壁面冷却に使用していた空気を燃焼用に使用することで、ガスタービンの高温下にもかかわらず予混合燃焼温度を空冷式燃焼器なみに抑えて低ＮＯX化が可能となるのである。
【０００３】
このような蒸気冷却は、例えば図７に示すように、パイロット燃料と燃焼用空気とが反応して拡散火炎を形成するコーン１の周囲に、メイン燃料と燃焼用空気との予混合気体を形成・噴出する予混合火炎形成ノズル２を複数に分割・配置してなるマルチノズル形予混合式燃焼器３の尾筒４の冷却に採用される。
【０００４】
これによれば、冷却蒸気は尾筒４の壁面内部に形成した冷却ジャケット５（図８参照）及びマニホールド６ａ，６ｂ，６ｃにより、先ず、尾筒４の長手方向中間部（マニホールド６ｂ参照）に供給され、ここから図中矢印のようにガス流れの上流側と下流側に分流されて壁面を冷却した後、尾筒４の入口部（マニホールド６ａ参照）と出口部（マニホールド６ｃ参照）から回収されるようになっている。尚、冷却蒸気の流れとしては、尾筒４の入口部（マニホールド６ａ参照）と出口部（マニホールド６ｃ参照）より供給された冷却蒸気が中間部（マニホールド６ｂ参照）に向け流れ、壁面を冷却した後、当該中間部から回収される所謂逆流方式のものもある。
【０００５】
また、冷却ジャケット５は、図８に示すように、二重壁で構成された尾筒４の一方壁４ａに溝巾Ｄ1 ＝溝深さＤ2 の溝加工を施す（溝加工部イ参照）と共に該溝加工した側に他方壁４ｂをロー付けする（ロー付け部ロ参照）ことで形成される。
【０００６】
【発明が解決しようとする課題】
ところが、前述したような従来の燃焼器尾筒の冷却構造にあっては、一般に出口部側が矩形状に形成された尾筒４の外周面（車室側）より内周面（ロータ側）及び側面（隣接する尾筒同志の対向面）のメタル温度が高くなる等で局所的に温度条件が異なるにもかかわらず、冷却ジャケット５のサイズ（通路断面積）が全周均一に設定されるなどして、各部への冷却蒸気の流量配分がメタル温度に関係なくなされているため、メタル温度不均一による熱応力の増大と尾筒４出口部（特に、フランジ部）の冷却不足による熱変形により、尾筒４出口部の四隅にクラックが発生するという問題点があった。
【０００７】
本発明は、前述した状況に鑑みてなされたもので、熱応力の軽減と熱変形の防止により尾筒クラックの発生を未然に回避することができて使用寿命の延命が図れる燃焼器尾筒の冷却構造を提供することを目的とする。
【０００８】
【課題を解決するための手段】
斯かる目的を達成するための本発明に係る燃焼器尾筒の冷却構造は、ガスタービン燃焼器の尾筒長手方向に冷却媒体の入口側マニホールドから出口側マニホールドへと延びる冷却ジャケットを尾筒壁面の全周に亙って多数本形成した燃焼器尾筒の冷却構造において、前記尾筒の出口部周縁に付設したフランジの正面部に前記出口部を囲繞するように環状の冷却通路を形成し、前記冷却通路に通じる複数の冷却媒体溜めを前記フランジの根元部に近接して尾筒の出口部周縁に複数設け、これらの冷却媒体溜めに前記冷却ジャケットをバイパスする複数本のバイパス冷却媒体ジャケットを介して冷却媒体が供給される一方、前記冷却通路を流れてフランジを冷却した冷却媒体は、前記冷却ジャケットを流れて尾筒壁面を冷却した冷却媒体と前記尾筒の出口部周縁に設けた前記出口側マニホールドで混合されて回収されることを特徴とする。
【００１３】
【発明の実施の形態】
以下、本発明に係る燃焼器尾筒の冷却構造を実施例により図面を用いて詳細に説明する。
【００１４】
［第１実施例］
図１は本発明の第１実施例を示す冷却ジャケットの断面積比較及びジャケット配置箇所を示す比較説明図で、同図（ａ）は現状冷却ジャケットサイズの説明図、同図（ｂ）は本発明冷却ジャケットサイズの説明図、同図（ｃ）は尾筒の要部切欠き斜視図で、同図（ａ）には一部切欠きで冷却ジャケットの通路を示している。
【００１５】
図１に示すように、本実施例では、出口部側が矩形状に形成された尾筒４の壁面内部に形成される冷却ジャケット（図８の符号５参照）は、その通路断面積が現状の冷却ジャケットより大部分において拡大されると共に、尾筒４各部のメタル温度に応じて例えば尾筒４の外周面（車室側）Ａと内周面（ロータ側）Ｂ及び側面（隣接する尾筒同志の対向面）Ｃとで、それぞれ通路断面積を変化させている。
【００１６】
即ち、現状の冷却ジャケットでは、図１の（ａ）に示すように、外周面、内周面及び側面において、例えば溝深さＤ2 （図８参照）＝φmmの均一の冷却ジャケットサイズに設定されるのに対し、本実施例では、図１の（ｂ）に示すように、外周面の中央部では溝深さＤ2 ＝φmmで、両側部（コーナー部）は溝深さＤ2 ≒１．０７φmmに冷却ジャケットサイズが設定されると共に、内周面では溝深さＤ2 ≒１．２１φmmに、かつ側面上流側では溝深さＤ2 ≒１．２９φmmに冷却ジャケットサイズが設定される。一方、側面下流側では溝深さＤ2 ≒１．０７φmmに冷却ジャケットサイズが設定される。尚、冷却ジャケットの本数は、現状と本実施例とで変化はない。
【００１７】
このようにして、本実施例では、尾筒４各部のメタル温度が均一になるように、各部の冷却ジャケットサイズを変化させて、冷却媒体としての冷却蒸気の流量配分を最適化したので、メタル温度不均一による熱応力の増大と尾筒４出口部の冷却不足による熱変形を効果的に防止でき、依って尾筒４出口部のクラック発生が回避される。
【００１８】
尚、上記実施例において、溝深さＤ2 に代えて又は溝深さＤ2 と共に溝巾Ｄ1 も増大するなどして各部の冷却ジャケットサイズを変化させても良い。
【００１９】
［第２実施例］
図２は本発明の第２実施例を示す尾筒出口部の比較説明図で、同図（ａ）は現状尾筒出口部の構造説明図、同図（ｂ）は本発明尾筒出口部の構造説明図である。尾筒全体の構造は図７を参照して詳しい説明は省略する。
【００２０】
図２に示すように、本実施例では、前述した尾筒４の出口部周縁（開口部周縁）に外向きに張出し形成されたフランジ４ａへ冷却蒸気を供給する冷却ジャケット５（図８参照）の行き先変更がなされて、前記フランジ４ａが積極的に蒸気冷却されるようになっている。
【００２１】
即ち、現状の冷却ジャケット５では、図２の（ａ）に示すように、前記フランジ４ａの根元部に送られた冷却蒸気は、前記根元部で隣の冷却ジャケット５へ流れた後上流側へ若干リターンして通孔５ａ（冷却ジャケット５の一本おきに形成される）よりマニホールド６ｃ内に流入するのに対し、本実施例では、図２の（ｂ）に示すように、前記フランジ４ａの根元部に送られた冷却蒸気は、前記フランジ４ａの高さ方向へ延設された通路５ｂを流れた後、マニホールド６ｃ内に流入するようになっている。従って、前記通路５ｂは、通孔５ａと異なり冷却ジャケット５の一本毎に形成される。
【００２２】
このようにして、本実施例では、尾筒４出口部のフランジ４ａ全体に冷却蒸気が行き渡るようにして、前記フランジ４ａの冷却強化を図ったので、温度差による熱変形を効果的に防止でき、依って尾筒４出口部のクラック発生が回避される。
【００２３】
［第３実施例］
図３は本発明の第３実施例を示す尾筒の要部側面図、図４は同じく尾筒出口部の背部斜視図、図５は同じく尾筒出口部の正面図、図６は図５のVI−VI線断面図である。
【００２４】
図３乃至図６に示すように、本実施例では、出口部側が矩形状に形成された尾筒４の壁面内部に形成される冷却ジャケット（図８の符号５参照）とは別に、バイパス蒸気ジャケット１０ａ〜１０ｄが設けられ、該バイパス蒸気ジャケット１０ａ〜１０ｄにより尾筒４の壁面を冷却しない冷却蒸気が、尾筒４出口部のフランジ４ａ正面に形成された環状の冷却通路１１に供給されて、前記フランジ４ａが積極的に蒸気冷却されるようになっている。
【００２５】
即ち、前記バイパス蒸気ジャケット１０ａ〜１０ｄは、前述したマニホールド６ｂから尾筒４の外周面に沿って周方向４本宛分岐されて尾筒４出口部の四隅に形成された蒸気溜め１２ａ〜１２ｄに通じている。該蒸気溜め１２ａ〜１２ｄは、前記矩形状フランジ４ａの四隅に形成された通孔１３ａ〜１３ｄ及び溝通路１４ａ〜１４ｄを介して前記冷却通路１１に通じている。そして、該冷却通路１１からは、周方向４ヶ所に設けた小孔群１５ａ〜１５ｄを介して前述したマニホールド６ｃに冷却蒸気は導かれ、ここで前記冷却ジャケット５からの冷却蒸気と混ざり、回収されるようになっている。尚、図中１６は冷却通路１１及び溝通路１４ａ〜１４ｄをそれらの溝加工後に閉塞する蓋板である。
【００２６】
このようにして、本実施例では、尾筒４出口部のフランジ４ａが、マニホールド６ｂからバイパス蒸気ジャケット１０ａ〜１０ｄ→蒸気溜め１２ａ〜１２ｄ→通孔１３ａ〜１３ｄ及び溝通路１４ａ〜１４ｄを介して熱交換なしで環状の冷却通路１１に供給される低温の冷却蒸気で、全体的に蒸気冷却されるため、十分な冷却効果が得られ、温度差による熱変形を防止して尾筒４出口部のクラック発生が回避される。
【００２７】
尚、本発明は上記各実施例に限定されず、本発明の要旨を逸脱しない範囲で、冷却媒体として空気を用いたり、第１〜第３実施例を同時に実施する（図２の（ｂ）参照）等各種変更が可能であることはいうまでもない。
【００２８】
【発明の効果】
以上、実施例に基づいて詳細に説明したように、本発明によれば、ガスタービン燃焼器の尾筒長手方向に冷却媒体の入口側マニホールドから出口側マニホールドへと延びる冷却ジャケットを尾筒壁面の全周に亙って多数本形成した燃焼器尾筒の冷却構造において、前記尾筒の出口部周縁に付設したフランジの正面部に前記出口部を囲繞するように環状の冷却通路を形成し、前記冷却通路に通じる複数の冷却媒体溜めを前記フランジの根元部に近接して尾筒の出口部周縁に複数設け、これらの冷却媒体溜めに前記冷却ジャケットをバイパスする複数本のバイパス冷却媒体ジャケットを介して冷却媒体が供給される一方、前記冷却通路を流れてフランジを冷却した冷却媒体は、前記冷却ジャケットを流れて尾筒壁面を冷却した冷却媒体と前記尾筒の出口部周縁に設けた前記出口側マニホールドで混合されて回収されることを特徴とするので、十分な冷却効果が得られ、温度差による熱変形を防止して尾筒出口部のクラック発生が回避されるという効果が得られる。
【図面の簡単な説明】
【図１】本発明の第１実施例を示す冷却ジャケットの比較説明図で、同図（ａ）は現状冷却ジャケットサイズの説明図、同図（ｂ）は本発明冷却ジャケットサイズの説明図、同図（ｃ）は尾筒の要部切欠き斜視図で、同図（ａ）には一部切欠きで冷却ジャケットの通路を示している。
【図２】本発明の第２実施例を示す尾筒出口部の比較説明図で、同図（ａ）は現状尾筒出口部の構造説明図、同図（ｂ）は本発明尾筒出口部の構造説明図である。
【図３】本発明の第３実施例を示す尾筒の要部側面図である。
【図４】同じく尾筒出口部の背部斜視図である。
【図５】同じく尾筒出口部の正面図である。
【図６】同じく図５のVI−VI線断面図である。
【図７】従来例を示すガスタービン燃焼器周りの側断面図である。
【図８】同じく図７のVIII−VIII線断面図である。
【符号の説明】
１ コーン
２ 予混合火炎形成ノズル
３ マルチノズル形予混合式燃焼器
４ 尾筒
４ａ フランジ
５ 冷却ジャケット
５ａ 通孔
５ｂ 通路
６ａ，６ｂ，６ｃ マニホールド
１０ａ〜１０ｄ バイパス蒸気ジャケット
１１冷却通路
１２ａ〜１２ｄ 蒸気溜め
１３ａ〜１３ｄ 通孔
１４ａ〜１４ｄ 溝通路
１５ａ〜１５ｄ 小孔群
１６ 蓋板
イ 溝加工部
ロ ロー付け部[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a cooling structure for a combustor tail cylinder for a gas turbine.
[0002]
[Prior art]
In recent years, as a gas turbine combustor, for example, a steam-cooled combustor that can achieve low NO x even with a 1500 ° C. class gas turbine has attracted attention. That is, by cooling the combustor wall surface with steam, the air previously used for wall surface cooling is used for combustion, so that the premixed combustion temperature can be set to the air-cooled combustor despite the high temperature of the gas turbine. it is the low NO X reduction is possible by suppressing the tears.
[0003]
For example, as shown in FIG. 7, the steam cooling forms a premixed gas of main fuel and combustion air around the cone 1 where the pilot fuel and combustion air react to form a diffusion flame. -It is employ | adopted for cooling of the tail cylinder 4 of the multi-nozzle type premix type combustor 3 which divides and arrange | positions the premixed flame formation nozzle 2 to eject.
[0004]
According to this, the cooling steam is first introduced into the longitudinal intermediate portion (see the manifold 6b) of the tail tube 4 by the cooling jacket 5 (see FIG. 8) and the manifolds 6a, 6b, 6c formed inside the wall surface of the tail tube 4. After being supplied and diverted to the upstream side and downstream side of the gas flow as shown by the arrows in the figure to cool the wall surface, it is recovered from the inlet portion (see the manifold 6a) and outlet portion (see the manifold 6c) of the tail cylinder 4 It has come to be. As the flow of the cooling steam, the cooling steam supplied from the inlet part (refer to the manifold 6a) and the outlet part (refer to the manifold 6c) of the transition piece 4 flows toward the intermediate part (refer to the manifold 6b) to cool the wall surface. There is also a so-called reverse flow type that is later recovered from the intermediate portion.
[0005]
Further, as shown in FIG. 8, the cooling jacket 5 performs the groove processing of the groove width D 1 = the groove depth D 2 on the one wall 4 a of the tail cylinder 4 formed of a double wall (see the groove processing portion a). ) And the other wall 4b is brazed to the grooved side (see brazed portion B).
[0006]
[Problems to be solved by the invention]
However, in the conventional cooling structure for the combustor tail cylinder as described above, the inner peripheral surface (rotor side) and the outer peripheral surface (chamber side) of the tail cylinder 4 whose outlet side is generally formed in a rectangular shape are generally provided. The size of the cooling jacket 5 (passage cross-sectional area) is set to be uniform even though the temperature conditions are locally different, such as the metal temperature on the side surfaces (opposite surfaces of adjacent tail cylinders) increases. Since the distribution of the flow rate of the cooling steam to each part is made regardless of the metal temperature, an increase in thermal stress due to non-uniform metal temperature and thermal deformation due to insufficient cooling of the tail tube 4 outlet part (particularly the flange part) There was a problem that cracks occurred at the four corners of the outlet portion of the transition piece 4.
[0007]
The present invention has been made in view of the above-described situation, and is a combustor tail tube that can avoid the occurrence of a tail tube crack by reducing thermal stress and preventing thermal deformation, thereby extending the service life of the combustor. An object is to provide a cooling structure.
[0008]
[Means for Solving the Problems]
In order to achieve such an object, a cooling structure for a combustor tail cylinder according to the present invention includes a cooling jacket extending from the inlet side manifold to the outlet side manifold of the cooling medium in the longitudinal direction of the tail cylinder of the gas turbine combustor. In the cooling structure for the combustor tail tube formed over the entire circumference, an annular cooling passage is formed so as to surround the outlet portion at the front portion of the flange attached to the periphery of the outlet portion of the tail tube. A plurality of cooling medium reservoirs communicating with the cooling passage are provided near the periphery of the flange and at the periphery of the outlet of the tail tube, and a plurality of bypass cooling medium jackets bypassing the cooling jacket to these cooling medium reservoirs while cooling medium is supplied through the cooling coolant passage to cool the flange flows, the cooling medium after cooling the tail tube wall flows through the cooling jacket tail Are mixed in the outlet-side manifold which is provided on the outlet peripheral edge, characterized in that it is recovered.
[0013]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, a cooling structure for a combustor tail cylinder according to the present invention will be described in detail with reference to the accompanying drawings.
[0014]
[First embodiment]
FIG. 1 is a cross-sectional area comparison of cooling jackets showing a first embodiment of the present invention and a comparative explanatory view showing jacket placement locations. FIG. 1 (a) is an explanatory view of the current cooling jacket size, and FIG. An explanatory view of the cooling jacket size of the invention, FIG. 2C is a perspective cutaway view of the main part of the tail tube, and FIG. 1A shows a passage of the cooling jacket with a partial cutout.
[0015]
As shown in FIG. 1, in this embodiment, the cooling jacket (see reference numeral 5 in FIG. 8) formed inside the wall surface of the tail cylinder 4 whose outlet portion side is formed in a rectangular shape has a current passage cross-sectional area. For example, the outer peripheral surface (chamber side) A and the inner peripheral surface (rotor side) B and the side surfaces (adjacent tail cylinders) of the tail cylinder 4 are expanded depending on the metal temperature of each part of the tail cylinder 4. The cross-sectional area of each of the opposite surfaces (C) is changed.
[0016]
That is, in the current cooling jacket, as shown in FIG. 1A, on the outer peripheral surface, the inner peripheral surface and the side surface, for example, the groove depth D 2 (see FIG. 8) is set to a uniform cooling jacket size of φmm. On the other hand, in this embodiment, as shown in FIG. 1B, the groove depth D 2 = φmm at the central portion of the outer peripheral surface and the groove depth D 2 ≈ on both sides (corner portions). the cooling jacket size is set to 1.07Faimm, cooling jacket size is set to the groove depth D 2 ≒ 1.29φmm in the groove depth D 2 ≒ 1.21φmm, and side upstream in the inner peripheral surface . On the other hand, on the downstream side of the side surface, the cooling jacket size is set to a groove depth D 2 ≈1.07 φmm. The number of cooling jackets does not change between the current state and the present embodiment.
[0017]
Thus, in this embodiment, the cooling jacket size of each part is changed so that the metal temperature of each part of the tail cylinder 4 is uniform, and the flow distribution of the cooling steam as the cooling medium is optimized. An increase in thermal stress due to temperature non-uniformity and thermal deformation due to insufficient cooling of the outlet portion of the transition piece 4 can be effectively prevented, and therefore the occurrence of cracks at the outlet portion of the transition piece 4 can be avoided.
[0018]
In the above embodiment, instead of the groove depth D 2 or with the groove depth D 2 groove width D 1 also may change the cooling jacket size of each part and the like increases.
[0019]
[Second Embodiment]
FIG. 2 is a comparative explanatory view of a transition piece outlet portion showing a second embodiment of the present invention. FIG. 2 (a) is a structural explanatory view of a current transition piece outlet portion, and FIG. FIG. Detailed description of the structure of the entire transition piece will be omitted with reference to FIG.
[0020]
As shown in FIG. 2, in this embodiment, the cooling jacket 5 (see FIG. 8) that supplies cooling steam to a flange 4 a that extends outwardly on the peripheral edge of the outlet portion (opening peripheral edge) of the tail cylinder 4 described above. The destination 4 is changed so that the flange 4a is actively steam-cooled.
[0021]
That is, in the current cooling jacket 5, as shown in FIG. 2A, the cooling steam sent to the root portion of the flange 4 a flows to the adjacent cooling jacket 5 at the root portion and then goes upstream. In the present embodiment, as shown in FIG. 2B, the flange 4a is slightly returned to flow into the manifold 6c through the through holes 5a (formed every other cooling jacket 5). The cooling steam sent to the root portion of the gas flows through the passage 5b extending in the height direction of the flange 4a and then flows into the manifold 6c. Accordingly, the passage 5b is formed for each cooling jacket 5 unlike the through hole 5a.
[0022]
In this way, in this embodiment, the cooling steam is spread over the entire flange 4a at the outlet portion of the transition piece 4 so as to enhance the cooling of the flange 4a, so that thermal deformation due to a temperature difference can be effectively prevented. Therefore, the occurrence of cracks at the exit portion of the transition piece 4 is avoided.
[0023]
[Third embodiment]
FIG. 3 is a side view of the main part of the transition piece according to the third embodiment of the present invention, FIG. 4 is a rear perspective view of the transition piece outlet part, FIG. 5 is a front view of the transition piece outlet part, and FIG. It is VI-VI sectional view taken on the line.
[0024]
As shown in FIGS. 3 to 6, in this embodiment, the bypass steam is separated from the cooling jacket (see reference numeral 5 in FIG. 8) formed inside the wall surface of the tail cylinder 4 in which the outlet side is formed in a rectangular shape. Jackets 10a to 10d are provided, and cooling steam that does not cool the wall surface of the tail cylinder 4 by the bypass steam jackets 10a to 10d is supplied to an annular cooling passage 11 formed in front of the flange 4a of the tail cylinder 4 outlet portion. The flange 4a is actively steam-cooled.
[0025]
That is, the bypass steam jackets 10a to 10d are branched into four steam reservoirs 12a to 12d which are branched from the manifold 6b to the circumferential direction along the outer peripheral surface of the tail cylinder 4 and are formed at the four corners of the outlet section of the tail cylinder 4. Communicates. The steam reservoirs 12a to 12d communicate with the cooling passage 11 through through holes 13a to 13d and groove passages 14a to 14d formed at the four corners of the rectangular flange 4a. And from this cooling channel | path 11, cooling steam is guide | induced to the manifold 6c mentioned above via the small hole groups 15a-15d provided in the circumferential direction four places, and here, it mixes with the cooling steam from the said cooling jacket 5, and is collect | recovered. It has come to be. In the figure, reference numeral 16 denotes a cover plate for closing the cooling passage 11 and the groove passages 14a to 14d after the grooves are processed.
[0026]
In this way, in the present embodiment, the flange 4a at the outlet portion of the transition piece 4 passes from the manifold 6b via the bypass steam jackets 10a to 10d → the steam reservoirs 12a to 12d → the through holes 13a to 13d and the groove passages 14a to 14d. The low-temperature cooling steam supplied to the annular cooling passage 11 without heat exchange is entirely cooled by steam, so that a sufficient cooling effect is obtained, and thermal deformation due to a temperature difference is prevented to prevent the tail tube 4 outlet portion. Generation of cracks is avoided.
[0027]
The present invention is not limited to the above embodiments, and air is used as a cooling medium or the first to third embodiments are simultaneously performed without departing from the gist of the present invention ((b) of FIG. 2). It goes without saying that various changes can be made.
[0028]
【The invention's effect】
As described above in detail based on the embodiment, according to the present invention, the cooling jacket extending from the inlet side manifold of the cooling medium to the outlet side manifold in the longitudinal direction of the tail cylinder of the gas turbine combustor is provided on the tail cylinder wall surface. In the cooling structure of the combustor tail tube formed over the entire circumference, an annular cooling passage is formed so as to surround the outlet portion at the front portion of the flange attached to the periphery of the outlet portion of the tail tube, A plurality of cooling medium reservoirs communicating with the cooling passage are provided at the periphery of the outlet portion of the tail tube adjacent to the base of the flange, and a plurality of bypass cooling medium jackets bypassing the cooling jacket are provided in these cooling medium reservoirs. while cooling medium is supplied through the cooling medium to and the cooling passage flow flange cooling, the transition piece and the coolant which has cooled the transition piece wall flows through said cooling jacket Because characterized in that it is recovered are mixed in the outlet-side manifold which is provided on the outlet peripheral edge, a sufficient cooling effect is obtained and cracking of the tail tube outlet portion avoided by preventing thermal deformation due to temperature difference The effect that it is done is acquired.
[Brief description of the drawings]
FIG. 1 is a comparative explanatory view of a cooling jacket showing a first embodiment of the present invention, where FIG. 1 (a) is an explanatory view of a current cooling jacket size, and FIG. 1 (b) is an explanatory view of a cooling jacket size of the present invention; FIG. 4C is a perspective view of the main part of the tail tube, with the main part cut away, and FIG.
FIGS. 2A and 2B are comparative explanatory views of a transition piece outlet portion showing a second embodiment of the present invention, in which FIG. 2A is a structural explanatory view of a current transition piece outlet portion, and FIG. It is structure explanatory drawing of a part.
FIG. 3 is a side view of an essential part of a transition piece showing a third embodiment of the present invention.
FIG. 4 is a rear perspective view of the tail tube outlet portion.
FIG. 5 is a front view of the transition piece outlet portion.
6 is a cross-sectional view taken along the line VI-VI in FIG.
FIG. 7 is a side sectional view around a gas turbine combustor showing a conventional example.
8 is a cross-sectional view taken along the line VIII-VIII in FIG.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Cone 2 Premixing flame formation nozzle 3 Multi-nozzle type premixing combustor 4 Cylinder 4a Flange 5 Cooling jacket 5a Through-hole 5b Passage 6a, 6b, 6c Manifold 10a-10d Bypass steam jacket 11 Cooling passage 12a-12d Steam reservoir 13a to 13d Through-holes 14a to 14d Groove passages 15a to 15d Small hole group 16 Lid plate A Groove processing part Roll attaching part

Claims (1)

ガスタービン燃焼器の尾筒長手方向に冷却媒体の入口側マニホールドから出口側マニホールドへと延びる冷却ジャケットを尾筒壁面の全周に亙って多数本形成した燃焼器尾筒の冷却構造において、
前記尾筒の出口部周縁に付設したフランジの正面部に前記出口部を囲繞するように環状の冷却通路を形成し、
前記冷却通路に通じる複数の冷却媒体溜めを前記フランジの根元部に近接して尾筒の出口部周縁に複数設け、
これらの冷却媒体溜めに前記冷却ジャケットをバイパスする複数本のバイパス冷却媒体ジャケットを介して冷却媒体が供給される一方、
前記冷却通路を流れてフランジを冷却した冷却媒体は、前記冷却ジャケットを流れて尾筒壁面を冷却した冷却媒体と前記尾筒の出口部周縁に設けた前記出口側マニホールドで混合されて回収されることを特徴とする燃焼器尾筒の冷却構造。In the cooling structure of the combustor tail cylinder in which a number of cooling jackets extending from the inlet side manifold of the cooling medium to the outlet side manifold in the longitudinal direction of the gas turbine combustor are formed over the entire circumference of the tail cylinder wall surface,
An annular cooling passage is formed so as to surround the outlet portion in the front portion of the flange attached to the periphery of the outlet portion of the tail tube,
Providing a plurality of cooling medium reservoirs communicating with the cooling passage on the periphery of the outlet portion of the tail tube in the vicinity of the base portion of the flange ,
While the cooling medium is supplied to the cooling medium reservoir through a plurality of bypass cooling medium jackets that bypass the cooling jacket ,
The cooling medium that has flowed through the cooling passage and cooled the flange is mixed and recovered by the cooling medium that has flowed through the cooling jacket and cooled the wall of the tail tube and the outlet side manifold provided at the periphery of the outlet of the tail tube. Combustor tail cylinder cooling structure characterized by the above.
JP2000152426A 2000-04-13 2000-05-24 Combustor tail cooling structure Expired - Lifetime JP4240759B2 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
JP2000152426A JP4240759B2 (en) 2000-05-24 2000-05-24 Combustor tail cooling structure
DE60137099T DE60137099D1 (en) 2000-04-13 2001-04-02 Cooling structure for the end of a gas turbine combustor
EP01108310A EP1146289B1 (en) 2000-04-13 2001-04-02 Cooling structure of combustor tail tube
CA002344012A CA2344012C (en) 2000-04-13 2001-04-12 Cooling structure of combustor tail tube
US09/832,937 US6553766B2 (en) 2000-04-13 2001-04-12 Cooling structure of a combustor tail tube

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2000152426A JP4240759B2 (en) 2000-05-24 2000-05-24 Combustor tail cooling structure

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JP5484707B2 (en) * 2008-10-10 2014-05-07 三菱重工業株式会社 Combustor and gas turbine
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