JP2014511991A - Combustion chamber housing and gas turbine including the same - Google Patents
Combustion chamber housing and gas turbine including the same Download PDFInfo
- Publication number
- JP2014511991A JP2014511991A JP2014505582A JP2014505582A JP2014511991A JP 2014511991 A JP2014511991 A JP 2014511991A JP 2014505582 A JP2014505582 A JP 2014505582A JP 2014505582 A JP2014505582 A JP 2014505582A JP 2014511991 A JP2014511991 A JP 2014511991A
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- Japan
- Prior art keywords
- combustion chamber
- flow guide
- chamber housing
- tube
- guide ribs
- 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
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 59
- 239000000779 smoke Substances 0.000 claims abstract description 52
- 238000005253 cladding Methods 0.000 claims abstract description 45
- 238000001816 cooling Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M9/00—Baffles or deflectors for air or combustion products; Flame shields
- F23M9/02—Baffles or deflectors for air or combustion products; Flame shields in air inlets
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03041—Effusion cooled combustion chamber walls or domes
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
燃焼室ハウジング(10)及び該燃焼室ハウジング(10)を備えるガスタービン(1)であって、前記燃焼室ハウジングは煙管(20)及び被覆管(30)を有し、該被覆管(30)は前記煙管(20)を包囲しており、また前記被覆管(30)の壁には複数の貫通穴(31)が設けられていて、外側において前記被覆管に向かって流れる空気がこれら貫通穴(31)を介して半径方向に、前記被覆管と前記煙管との間に形成された中間空間(40)に流入できる。本発明により、前記煙管の周囲に流入する空気の分布がより均一になる。これは特に、中間空間において2つの管の円周方向に複数のガイドリブ(50)を分配して配置し、これらガイドリブ(50)はそれぞれ被覆管と煙管との間では半径方向に、2つの管の長手方向(LR)に対しては平行に延在させ、それにより、中間空間をガイドリブにより複数の長手方向管(41)に分割することにより達成される。 A combustion chamber housing (10) and a gas turbine (1) comprising the combustion chamber housing (10), the combustion chamber housing having a smoke tube (20) and a cladding tube (30), the cladding tube (30) Encloses the smoke pipe (20), and a plurality of through holes (31) are provided in the wall of the cladding pipe (30), and the air flowing toward the cladding pipe on the outside is provided in the through holes. Through (31), it can flow into the intermediate space (40) formed between the cladding tube and the smoke tube in the radial direction. According to the present invention, the distribution of air flowing around the smoke pipe becomes more uniform. In particular, the guide ribs (50) are distributed and arranged in the circumferential direction of the two tubes in the intermediate space, and these guide ribs (50) are arranged in the radial direction between the cladding tube and the smoke tube, respectively. This is achieved by extending parallel to the longitudinal direction (LR) of the tube and thereby dividing the intermediate space into a plurality of longitudinal tubes (41) by guide ribs.
Description
本発明は、請求項1に記載の燃焼室ハウジング及びそのような燃焼室ハウジングを有するガスタービンに関する。 The invention relates to a combustion chamber housing according to claim 1 and a gas turbine comprising such a combustion chamber housing.
上記のような燃焼室ハウジング及びガスタービンは、たとえば特許文献1より既知である。そこに記載されている燃焼室ハウジングは、ガスタービンの燃焼室の構成要素であり、煙管、及び、被覆管又はバッフルスクリーンを有しており、該被覆管又はバッフルスクリーンは煙管を取り囲んでいて、その壁には複数の貫通穴が設けられており、外側において被覆管に向かって流れる圧縮空気がこれら貫通穴を通って半径方向に、被覆管と煙管との間に形成された中間空間内に流入できる。 The combustion chamber housing and the gas turbine as described above are known from, for example, Patent Document 1. The combustion chamber housing described therein is a component of a combustion chamber of a gas turbine and has a smoke tube and a cladding tube or baffle screen, the cladding tube or baffle screen surrounding the smoke tube, The wall is provided with a plurality of through holes, and compressed air that flows toward the cladding tube on the outside passes through these through holes in a radial direction, in an intermediate space formed between the cladding tube and the smoke tube. Inflow.
燃焼室は、単独モジュールとして、又はリング状に配置された単独燃焼器として、又はリング状燃焼室として実施されている。リング状燃焼室を除き、これらのタイプは常に、内側に位置する、円筒状に構成された煙管を有している。 The combustion chamber is implemented as a single module, as a single combustor arranged in a ring, or as a ring combustion chamber. With the exception of the ring-shaped combustion chamber, these types always have a cylindrically configured smoke tube located inside.
上述のようなガスタービンにおいては、燃焼空気はまず大気圧で吸入され、それからガス発生器のコンプレッサ内で圧縮される。コンプレッサは半径方向又は軸方向に実施できる。そこから下流に後続する燃焼室において、燃焼ゾーン内へ向かう流れにするために燃焼空気は大きく方向転換される。換言すると、燃焼空気はまず燃焼室に対して半径方向に、被覆管と煙管との間に形成された中間空間内に供給され、次に方向転換されて、燃焼器へ向かう軸方向の流れが作られる。 In the gas turbine as described above, the combustion air is first sucked in at atmospheric pressure and then compressed in the compressor of the gas generator. The compressor can be implemented radially or axially. In the combustion chamber that follows downstream from there, the combustion air is largely redirected to flow into the combustion zone. In other words, the combustion air is first supplied in a radial direction with respect to the combustion chamber into an intermediate space formed between the cladding tube and the smoke tube and then redirected so that an axial flow towards the combustor is achieved. Made.
中間空間内においては、多くが円筒状である煙管の周囲の円周方向の流れ又は回転する流れが起こり、それにより、燃焼空気の圧力分布又は流量分布に関してよどみ点及び後流が生じる。そのような不均一な質量流分布においてさらに、流れが先述のように大きく方向転換されると、この不均一性は保たれる。それにより、下流に位置する構成部品の冷却が不均一になり、また、空気含有率が変化するため燃焼ゾーン内は不安定になる。 Within the intermediate space, there is a circumferential or rotating flow around the smoke tube, which is mostly cylindrical, thereby creating stagnation points and wakes with respect to the pressure distribution or flow distribution of the combustion air. In addition, in such a non-uniform mass flow distribution, this non-uniformity is maintained when the flow is greatly diverted as described above. Thereby, the cooling of the components located downstream becomes non-uniform, and the inside of the combustion zone becomes unstable because the air content changes.
本発明の課題は、煙管の周囲に流入する空気の分布をより均等にすることが保証される、請求項1に記載の燃焼室ハウジング及びこれを有するガスタービンを提供することである。 An object of the present invention is to provide a combustion chamber housing and a gas turbine having the same according to claim 1, wherein it is ensured that the distribution of air flowing around the smoke pipe is made more uniform.
このことは、請求項1に記載の燃焼室ハウジング又は請求項10に記載のガスタービンにより達成される。本発明の発展形は従属請求項で定義される。 This is achieved by a combustion chamber housing according to claim 1 or a gas turbine according to claim 10. Developments of the invention are defined in the dependent claims.
本発明の第1の態様においては、燃焼室ハウジング、特にガスタービン用の燃焼室ハウジングが提供され、該燃焼室ハウジングは望ましくは円筒状の煙管、及び望ましくは円筒状の被覆管又はバッフルスクリーンを有しており、該被覆管又はバッフルスクリーンは煙管を収容して包囲しており、また、その壁には複数の貫通穴があり、外側において被覆管に向かって流れる圧縮空気(冷却空気及び燃焼空気)がこの貫通穴を通じて半径方向に、被覆管と煙管との間に形成された、望ましくは円筒形の中間空間内に流入できる。本発明の燃焼室ハウジングは、中間空間内において両方の管(煙管及び被覆管)の円周方向に分配されて配置された複数のガイドリブを特徴としており、これらガイドリブはそれぞれ、被覆管と煙管との間では半径方向に延在し、また、被覆管及び煙管の長手方向に対して平行に、及び長手方向に沿って延在しているため、中間空間は、ガイドリブにより、貫通穴が設けられた被覆管の長さの望ましくはほぼ全体にわたって延在する、望ましくはそれぞれ円環扇形状の断面をもつ、複数の長手方向管に分割されている。 In a first aspect of the invention, there is provided a combustion chamber housing, particularly a combustion chamber housing for a gas turbine, which preferably has a cylindrical smoke tube, and preferably a cylindrical cladding tube or baffle screen. The cladding tube or baffle screen encloses and surrounds the smoke tube, and has a plurality of through holes in its wall, and compressed air (cooling air and combustion) flowing toward the cladding tube on the outside Air) can flow radially through the through-holes into a preferably cylindrical intermediate space formed between the cladding tube and the smoke tube. The combustion chamber housing of the present invention is characterized by a plurality of guide ribs that are distributed and arranged in the circumferential direction of both tubes (smoke tube and cladding tube) in the intermediate space, and these guide ribs are respectively a cladding tube and a smoke tube. The intermediate space is provided with a through-hole by a guide rib because it extends in the radial direction between and between and parallel to the longitudinal direction of the cladding tube and the smoke tube and along the longitudinal direction. The length of the coated tube is divided into a plurality of longitudinal tubes, preferably extending substantially over the entire length, preferably each having an annular sector cross section.
ガイドリブは、運転中に流入する空気が周囲を流れる方向に対して横方向に位置し、煙管の周囲の流れを中断又は阻害するようにはたらく。それにより、空気流はより均等に分配され、煙管の冷却もより妨げられなくなる。さらに、冷却空気及び燃焼空気は、半径方向の流れから軸方向の流れに方向転換された後は導管のように導かれるため、後続の燃焼ゾーンへ向かう流れが均質になる。 The guide ribs are located in a direction transverse to the direction in which air flowing in during operation flows, and serve to interrupt or inhibit the flow around the smoke pipe. Thereby, the air flow is more evenly distributed and the cooling of the smoke tube is less disturbed. Furthermore, the cooling air and the combustion air are guided like a conduit after being redirected from a radial flow to an axial flow, so that the flow toward the subsequent combustion zone is homogeneous.
空気の流入を最適化することにより、本発明の燃焼室ハウジングを備える、ガスタービンの燃焼室においては特に均質な空燃混合気を形成することができ、それにより、燃焼工程において炎が安定して燃焼室中心にとどまる。炎の傾き又は揺らぎがあると、周囲の構成部品の局所的な温度上昇を起こし、それにより過度の負荷が起こる場合もあるが、これはガイドリブにより回避される。 By optimizing the air inflow, a homogeneous air / fuel mixture can be formed, particularly in the combustion chamber of a gas turbine with the combustion chamber housing of the present invention, thereby stabilizing the flame in the combustion process. Stay in the center of the combustion chamber. Any tilt or fluctuation of the flame will cause a local temperature rise in the surrounding components, which may cause excessive loading, but this is avoided by the guide ribs.
その結果、ガスタービンの燃焼室において本発明により構成された燃焼室ハウジングを使用することにより、空気供給の不均一性が最小限に抑えられるため、最大設計温度での燃焼室の運転を制限なしで行うことができる。 As a result, the use of a combustion chamber housing constructed in accordance with the present invention in the combustion chamber of a gas turbine minimizes air supply non-uniformity, thus limiting the operation of the combustion chamber at the maximum design temperature. Can be done.
本発明においてガイドリブは望ましくは被覆管に取り付けられる。また、各ガイドリブは、望ましくはガイドリブと煙管との間に間隙が形成されるように、半径方向に延在している。 In the present invention, the guide rib is desirably attached to the cladding tube. Each guide rib extends radially so that a gap is preferably formed between the guide rib and the smoke pipe.
この間隙は、材料特性及び熱膨張特性が異なるために起こりうるゆがみ又は応力を回避するために好適である。流れが常に半径方向において外に向かって、流れガイドリブも取り付けられている側面(被覆管の内周)に向かうため、この間隙を通って生じる横断流は無視できる。 This gap is suitable to avoid distortions or stresses that can occur due to different material properties and thermal expansion properties. Since the flow is always directed radially outward and toward the side surface on which the flow guide ribs are also attached (inner circumference of the cladding tube), the cross flow generated through this gap is negligible.
本発明のガイドリブは望ましくはそれぞれ薄板状に構成されており、それぞれの幅は被覆管及び煙管の半径方向に、それぞれの長さは軸方向又は長手方向に延在する。それぞれのガイドリブの厚みは望ましくはおよそ3mmである。 The guide ribs of the present invention are preferably each formed in a thin plate shape, each width extending in the radial direction of the cladding tube and the smoke tube, and each length extending in the axial direction or the longitudinal direction. The thickness of each guide rib is desirably about 3 mm.
本発明のガイドリブ及び被覆管の壁内に形成された貫通穴は望ましくは、ガイドリブがいずれの貫通穴もふさぐことがないように配置されている。それにより好適に、中間空間への空気の半径方向の流れが最適に又は妨げられずに行われることが保証される。 The guide rib and the through hole formed in the wall of the cladding tube of the present invention are desirably arranged so that the guide rib does not block any through hole. This preferably ensures that the radial flow of air to the intermediate space takes place optimally or unimpeded.
本発明の望ましい実施形態によると、中間空間内に設けられたガイドリブの数は正確に8個であり、すべてのガイドリブは互いに同一の構成である。 According to a preferred embodiment of the present invention, the number of guide ribs provided in the intermediate space is exactly eight, and all the guide ribs have the same configuration.
本発明によると望ましくはガイドリブは中間空間内において互いに異なる円周方向の角距離をおいて配置される。角距離は望ましくはおよそ28度からおよそ126℃の範囲にある。 According to the present invention, the guide ribs are preferably arranged at different angular distances in the circumferential direction in the intermediate space. The angular distance is desirably in the range of approximately 28 degrees to approximately 126 degrees Celsius.
本発明において望ましくは、ガイドリブは第1ガイドリブ・グループ及び第2ガイドリブ・グループを有しており、第1ガイドリブ・グループは互いの円周方向の角距離に関して所与の第1配置パターンで配置されており、第2ガイドリブ・グループは互いの円周方向の角距離に関して第2配置パターンで配置されており、この第2配置パターンは、煙管の対称軸について第1配置パターンの鏡像となっている。望ましくはこの対称軸は断面から見て煙管の中心を通って延在している。 In the present invention, preferably, the guide rib has a first guide rib group and a second guide rib group, and the first guide rib group is arranged in a given first arrangement pattern with respect to a circumferential angular distance of each other. The second guide rib groups are arranged in a second arrangement pattern with respect to each other in the circumferential angular distance, and this second arrangement pattern is a mirror image of the first arrangement pattern with respect to the axis of symmetry of the smoke tube. . Preferably, this axis of symmetry extends through the center of the smoke tube as viewed in cross section.
本発明の第2の態様によるとガスタービンは、先述した本発明の燃焼室ハウジングの望ましい実施例の一つ、又は、複数、又はすべてを、あらゆる組み合わせで備えて提供される。 According to a second aspect of the present invention, a gas turbine is provided with one, more or all of the preferred embodiments of the combustion chamber housing of the present invention described above in any combination.
本発明には、明示的に引用された請求項の特徴の組み合わせによらない実施形態も含まれ、そのため、本発明の開示された特徴は、技術的に有意義である限り、互いに任意に組み合わせることができる。 The invention also includes embodiments that do not rely on the combination of the features of the explicitly cited claims, and therefore the disclosed features of the invention can be arbitrarily combined with each other as long as they are technically meaningful. Can do.
以下、本発明の実施の形態について、望ましい実施形態及び図を用いて詳細に説明する。 Hereinafter, embodiments of the present invention will be described in detail with reference to preferred embodiments and drawings.
図1から4を参照しながら、本発明の実施形態の燃焼室ハウジング10を持つガスタービン1(全体は図示されず)について以下に説明する。 A gas turbine 1 (not shown in its entirety) having a combustion chamber housing 10 according to an embodiment of the present invention will be described below with reference to FIGS.
ガスタービン1の燃焼室ハウジング10は、円筒状煙管20及び円筒状被覆管又はバッフルスクリーン30を有しており、該円筒状被覆管又はバッフルスクリーン30は煙管20を収容して周りを取り囲んでおり、また、円筒状被覆管又はバッフルスクリーン30の壁には、ぐるりと円周に沿って均等に分配された複数の貫通穴31が設けられており、外周において被覆管30に向かって流れる、ガスタービン1のコンプレッサ(図示されず)により圧縮された空気(冷却空気及び燃焼空気)が、これらの貫通穴31を介して半径方向に、被覆管30と煙管20との間に形成された円筒形の中間空間40内に流入できる。 The combustion chamber housing 10 of the gas turbine 1 has a cylindrical smoke tube 20 and a cylindrical cladding tube or baffle screen 30, and the cylindrical cladding tube or baffle screen 30 encloses and surrounds the smoke tube 20. In addition, the wall of the cylindrical cladding tube or baffle screen 30 is provided with a plurality of through holes 31 that are evenly distributed around the circumference and flows toward the cladding tube 30 on the outer periphery. A cylindrical shape in which air (cooling air and combustion air) compressed by a compressor (not shown) of the turbine 1 is formed between the cladding tube 30 and the smoke tube 20 in the radial direction through the through holes 31. Can flow into the intermediate space 40.
中間空間40内には、2つの管(煙管20及び被覆管30)の円周方向において分配されて配置された、複数の(ここでは正確に8個の)同一のガイドリブ50が設けられており、これらのガイドリブ50はそれぞれ被覆管30と煙管20との間では半径方向に、また、被覆管30及び煙管20の長手方向LRに対して平行に、また、長手方向LRに沿って延在しており、それにより、中間空間40はガイドリブ50により、貫通穴31が設けられた被覆管30の長さにわたってほぼ延在する、それぞれ円環扇形の断面を持つ複数の長手方向管41に分割される。 In the intermediate space 40, a plurality of (here, exactly eight) identical guide ribs 50 are provided which are distributed and arranged in the circumferential direction of the two tubes (the smoke tube 20 and the cladding tube 30). The guide ribs 50 extend in the radial direction between the cladding tube 30 and the smoke tube 20, parallel to the longitudinal direction LR of the cladding tube 30 and the smoke tube 20, and along the longitudinal direction LR. Accordingly, the intermediate space 40 is divided by the guide rib 50 into a plurality of longitudinal tubes 41 each having an annular fan-shaped cross section that extends substantially over the length of the cladding tube 30 provided with the through holes 31. The
ガイドリブ50があることにより、運転中に貫通穴31を介して半径方向に流入する空気に、中間空間40内で円周方向又は煙管20の周りを回転する流れの成分が生じることが確実に回避される。それにより、煙管20の周りの空気流をより均等に配分することができ、煙管20の冷却も改善される。さらに、空気は、(煙管20に衝突することにより)半径方向から軸方向の流れに方向転換された後、導管状に長手方向管41内を導かれ、それにより後続の燃焼ゾーン(図示されず)へ向かう流れを均質にできる。 Due to the presence of the guide rib 50, it is reliably avoided that air flowing in the radial direction through the through-hole 31 during operation generates a component of the flow rotating in the circumferential direction or around the smoke pipe 20 in the intermediate space 40. Is done. Thereby, the air flow around the smoke tube 20 can be more evenly distributed, and the cooling of the smoke tube 20 is also improved. Furthermore, the air is diverted from radial to axial flow (by impinging on the smoke tube 20) and then guided in a longitudinal manner in the longitudinal tube 41 so that a subsequent combustion zone (not shown) ) Can be made uniform.
ガイドリブ50は被覆管30の内周に取り付けられて(たとえば溶接されて)おり、各ガイドリブ50は、ガイドリブ50と煙管20との間に間隙Sが形成されるように、半径方向に延在している。間隙Sの半径方向の幅は、ガスタービン1の運転中における、煙管20、被覆管30及びガイドリブ50の、熱によるさまざまな材料膨張が、ガイドリブ50が煙管20に圧力をかけて押し付けられることなくちょうど補償できるような幅となっている。 The guide ribs 50 are attached (for example, welded) to the inner periphery of the cladding tube 30, and each guide rib 50 extends in the radial direction so that a gap S is formed between the guide rib 50 and the smoke tube 20. ing. The radial width of the gap S is such that, during operation of the gas turbine 1, various material expansions of the smoke tube 20, the cladding tube 30, and the guide rib 50 due to heat are not caused by the guide rib 50 being pressed against the smoke tube 20. The width is just enough to compensate.
ガイドリブ50はそれぞれ金属片の形に形成されており、ガイドリブ50のそれぞれの幅は被覆管30及び煙管20の半径方向に、また、それぞれの長さは軸方向又は長手方向LRに延在している。このときそれぞれのガイドリブ50の厚みはおよそ3mmである。 Each of the guide ribs 50 is formed in the shape of a metal piece. The width of each guide rib 50 extends in the radial direction of the cladding tube 30 and the smoke tube 20, and the length of each guide rib 50 extends in the axial direction or the longitudinal direction LR. Yes. At this time, the thickness of each guide rib 50 is about 3 mm.
特に図3(図の左半分)からわかるようにガイドリブ50及び、被覆管30の壁に形成された貫通穴31は、ガイドリブ50によりいずれの貫通穴31もふさがれることがないよう配置されている。 In particular, as can be seen from FIG. 3 (the left half of the figure), the guide rib 50 and the through hole 31 formed in the wall of the cladding tube 30 are arranged so that none of the through holes 31 are blocked by the guide rib 50. .
特に図1及び2からわかるようにガイドリブ50は互いに、異なる円周方向の角距離をおいて中間空間40内に配置されている。 As can be seen from FIGS. 1 and 2 in particular, the guide ribs 50 are arranged in the intermediate space 40 at different angular distances in the circumferential direction.
ガイドリブ50は、(図2において煙管20の対称軸Yの左に配置されている)ガイドリブ50の第1グループ、及び、(図2において対称軸Yの右に配置されている)ガイドリブ50の第2グループを有している。図示された本発明の実施形態によるとガイドリブ50の第1グループは、その互いの円周方向角距離に関して所与の第1配置パターンで配置されており、ガイドリブ50の第2グループは、その互いの円周方向角距離に関して第2配置パターンで配置されており、この第2配置パターンは、対称軸Yにおける第1配置パターンの鏡像である。 The guide rib 50 includes a first group of guide ribs 50 (arranged to the left of the symmetry axis Y of the smoke tube 20 in FIG. 2) and a first group of the guide ribs 50 (arranged to the right of the symmetry axis Y in FIG. 2). There are two groups. According to the illustrated embodiment of the present invention, the first group of guide ribs 50 are arranged in a given first arrangement pattern with respect to each other's circumferential angular distance, and the second group of guide ribs 50 is arranged with respect to each other. Are arranged in a second arrangement pattern with respect to the circumferential direction angular distance, and this second arrangement pattern is a mirror image of the first arrangement pattern in the symmetry axis Y.
図2に図示された本発明の実施形態によるとガイドリブ50の第1グループの所与の第1配置パターンは角度寸法a=27度、b=1.8度、c=34.2度、d=59.4度により定義される。ガイドリブ50の第2グループの第2配置パターンは、角度寸法a'=27度、b'=1.8度、c'=34.2度、d'=59.4度により定義される。 According to the embodiment of the present invention illustrated in FIG. 2, the given first arrangement pattern of the first group of guide ribs 50 has angular dimensions a = 27 degrees, b = 1.8 degrees, c = 34.2 degrees, d = 59.4 degrees. The second arrangement pattern of the second group of guide ribs 50 is defined by angular dimensions a ′ = 27 degrees, b ′ = 1.8 degrees, c ′ = 34.2 degrees, and d ′ = 59.4 degrees.
換言すると、図2によるとガイドリブ50の各グループにおいて、ガイドリブ50間の角距離は28.2度、32.4度、25.2度の組み合わせとなり、ガイドリブ50の両方のグループの角距離は61.2度(図2の下部)又は126度(図2の上部)となる。 In other words, according to FIG. 2, in each group of the guide ribs 50, the angular distance between the guide ribs 50 is a combination of 28.2 degrees, 32.4 degrees, and 25.2 degrees, and the angular distances of both groups of the guide ribs 50 are 61. 2 degrees (lower part of FIG. 2) or 126 degrees (upper part of FIG. 2).
図示されていない本発明の他の実施形態によると、第1及び第2配置パターンを完全に異なるものとすることも可能である。第1及び第2配置パターン又はガイドリブ50のそれぞれの角距離は、ガスタービン1のたとえば寸法上、及び/又は、形状上のそれぞれの実施形態に応じて特別に実現することができ、それにより、その際に生じる特別な流れの状況に適応させることができる。 According to another embodiment of the present invention not shown, the first and second arrangement patterns may be completely different. The respective angular distances of the first and second arrangement patterns or guide ribs 50 can be specially realized depending on the respective embodiment of the gas turbine 1, for example in terms of dimensions and / or shape, whereby It can be adapted to the special flow situation that occurs.
図4は、燃焼室ハウジング10内における空気の流れ及び圧力の分布の比較を2つの断面図で図示したもので、図4の上の図の燃焼室ハウジングにはガイドリブ50が設けられておらず、図4の下の図における本発明の燃焼室ハウジングにはガイドリブ50が設けられている。 FIG. 4 illustrates a comparison of air flow and pressure distribution in the combustion chamber housing 10 in two cross-sectional views. The combustion chamber housing in the upper diagram of FIG. 4 is not provided with the guide rib 50. 4 is provided with a guide rib 50 in the combustion chamber housing according to the present invention.
図4の上の図からわかるようにガイドリブ50がない場合、ガスタービン1の運転中において煙管20の円周方向の周囲の流れのために、中間空間40内の空気の流れ及び圧力の状態は不均一となる。 As can be seen from the upper diagram of FIG. 4, when there is no guide rib 50, the flow of air and the pressure state in the intermediate space 40 are due to the circumferential flow of the smoke pipe 20 during operation of the gas turbine 1. It becomes non-uniform.
図4の下の図からわかるように、ガスタービン1の運転中、流入する空気が周囲を流れる方向に対して横方向に位置するガイドリブ50により、煙管20の円周方向の周囲の流れが妨げられるため、中間空間40内の空気の流れ及び圧力の状態がほぼ均質になり、それにより、煙管20の周りに流入する空気が均等に分布し、煙管20の冷却が改善される。さらに、空気は、半径方向の流れから軸方向の流れに方向転換された後、導管状に導かれるため、後続の燃焼ゾーンへ向かう流れが均質になる。 As can be seen from the lower diagram of FIG. 4, during the operation of the gas turbine 1, the circumferential flow of the smoke tube 20 is obstructed by the guide ribs 50 that are located in a direction transverse to the direction in which the incoming air flows. As a result, the air flow and pressure conditions in the intermediate space 40 are substantially uniform, whereby the air flowing around the smoke tube 20 is evenly distributed and the cooling of the smoke tube 20 is improved. In addition, the air is redirected from a radial flow to an axial flow and then guided in a conduit, so that the flow toward the subsequent combustion zone is homogeneous.
1 ガスタービン
10 燃焼室ハウジング
20 煙管
30 被覆管
31 貫通穴
40 中間空間
41 長手方向管
50 ガイドリブ
S 間隙
LR 長手方向
Y 対称軸
a、b、c、d 角度寸法
a'、b'、c'、d' 角度寸法
DESCRIPTION OF SYMBOLS 1 Gas turbine 10 Combustion chamber housing 20 Smoke pipe 30 Cladding pipe 31 Through hole 40 Intermediate space 41 Longitudinal pipe 50 Guide rib S Gap LR Longitudinal direction Y Symmetry axis a, b, c, d Angular dimensions a ′, b ′, c ′, d 'Angular dimension
Claims (8)
前記中間空間(40)内において前記2つの管の円周方向に複数の流れガイドリブ(50)が分配されて配置されており、前記複数の流れガイドリブ(50)はそれぞれ、被覆管(30)と煙管(20)との間において半径方向に、また被覆管(30)及び煙管(20)の長手方向(LR)に対して平行に延在していて、その際前記複数の流れガイドリブ(50)は前記被覆管(30)にのみ固定されており、また、少なくとも前記ガスタービン(1)の休止状態において前記煙管(20)に対して間隙(S)が形成され、それにより前記中間空間(40)が前記流れガイドリブ(50)により複数の長手方向管(41)に分割されることを特徴とする、燃焼室ハウジング(10)。 A combustion chamber housing (10) of a gas turbine (1), comprising a smoke tube (20) and a cladding tube (30), the cladding tube (30) surrounding the smoke tube (20), The wall of the cladding tube (30) is provided with a plurality of through holes (31), and air flowing toward the cladding tube (30) on the outside passes through the plurality of through holes (31). In the combustion chamber housing (10) that can flow radially into the intermediate space (40) formed between the cladding tube (30) and the smoke tube (20),
A plurality of flow guide ribs (50) are distributed and arranged in the circumferential direction of the two pipes in the intermediate space (40), and the plurality of flow guide ribs (50) are respectively connected to the cladding pipe (30) and The plurality of flow guide ribs (50) extend radially between the smoke pipe (20) and parallel to the longitudinal direction (LR) of the cladding pipe (30) and the smoke pipe (20). Is fixed only to the cladding tube (30), and a gap (S) is formed with respect to the smoke tube (20) at least when the gas turbine (1) is at rest, whereby the intermediate space (40) is formed. ) Is divided into a plurality of longitudinal tubes (41) by the flow guide rib (50).
Applications Claiming Priority (3)
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DE102011007562A DE102011007562A1 (en) | 2011-04-18 | 2011-04-18 | Combustor housing and thus equipped gas turbine |
DE102011007562.3 | 2011-04-18 | ||
PCT/EP2012/056878 WO2012143318A1 (en) | 2011-04-18 | 2012-04-16 | Combustion chamber housing and gas turbine equipped therewith |
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JP2014511991A true JP2014511991A (en) | 2014-05-19 |
JP5678232B2 JP5678232B2 (en) | 2015-02-25 |
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JP2014505582A Active JP5678232B2 (en) | 2011-04-18 | 2012-04-16 | Combustion chamber housing and gas turbine including the same |
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US (1) | US20140144138A1 (en) |
EP (1) | EP2699848B1 (en) |
JP (1) | JP5678232B2 (en) |
CA (1) | CA2833464A1 (en) |
DE (1) | DE102011007562A1 (en) |
RU (1) | RU2544400C1 (en) |
WO (1) | WO2012143318A1 (en) |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE709065C (en) * | 1935-07-17 | 1941-08-07 | Rene Alexandre Arthur Couzinet | Feeding device for gas turbines |
JPS62118958U (en) * | 1986-01-16 | 1987-07-28 | ||
JPH1082527A (en) * | 1996-09-05 | 1998-03-31 | Toshiba Corp | Gas turbine combustor |
WO2011012126A2 (en) * | 2009-07-31 | 2011-02-03 | Man Diesel & Turbo Se | Gas turbine combustion chamber |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1004212B (en) | 1953-11-07 | 1957-03-14 | Westfalenhuette Ag | Process for the heat treatment of reinforcing steel |
US3915619A (en) * | 1972-03-27 | 1975-10-28 | Phillips Petroleum Co | Gas turbine combustors and method of operation |
GB1550368A (en) * | 1975-07-16 | 1979-08-15 | Rolls Royce | Laminated materials |
US4414816A (en) * | 1980-04-02 | 1983-11-15 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Combustor liner construction |
GB2087065B (en) * | 1980-11-08 | 1984-11-07 | Rolls Royce | Wall structure for a combustion chamber |
US5337568A (en) * | 1993-04-05 | 1994-08-16 | General Electric Company | Micro-grooved heat transfer wall |
DE4443864A1 (en) * | 1994-12-09 | 1996-06-13 | Abb Management Ag | Cooled wall part |
US5724816A (en) * | 1996-04-10 | 1998-03-10 | General Electric Company | Combustor for a gas turbine with cooling structure |
RU2138661C1 (en) * | 1996-05-22 | 1999-09-27 | Акционерное общество "Авиадвигатель" | Gas turbine engine operating on cryogenic fuel |
JP2002162036A (en) * | 2000-11-22 | 2002-06-07 | Mitsubishi Heavy Ind Ltd | Combustor |
JP2004524479A (en) * | 2001-04-27 | 2004-08-12 | シーメンス アクチエンゲゼルシヤフト | Especially for gas turbine combustion chambers |
EP1288574A1 (en) * | 2001-09-03 | 2003-03-05 | Siemens Aktiengesellschaft | Combustion chamber arrangement |
RU36724U1 (en) * | 2003-08-14 | 2004-03-20 | Государственное предприятие Запорожское машиностроительное конструкторское бюро "Прогресс" им. акад. А.Г. Ивченко | FRONT DEVICE OF COMBUSTION CHAMBER OF A GAS TURBINE ENGINE |
DE102004016462A1 (en) * | 2004-03-31 | 2005-11-24 | Alstom Technology Ltd | Coolable wall structure for especially gas turbine has cooling medium passing through passages formed in core and parallel to one another and parallel to inner and outer shells |
RU2280814C1 (en) * | 2004-12-27 | 2006-07-27 | Акционерное общество открытого типа Авиамоторный научно-технический комплекс "Союз" | Ring combustion chamber for gas-turbine engine |
DE102006042124B4 (en) * | 2006-09-07 | 2010-04-22 | Man Turbo Ag | Gas turbine combustor |
DE102007018061A1 (en) * | 2007-04-17 | 2008-10-23 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine combustion chamber wall |
-
2011
- 2011-04-18 DE DE102011007562A patent/DE102011007562A1/en not_active Withdrawn
-
2012
- 2012-04-16 JP JP2014505582A patent/JP5678232B2/en active Active
- 2012-04-16 RU RU2013151088/06A patent/RU2544400C1/en not_active IP Right Cessation
- 2012-04-16 US US14/112,464 patent/US20140144138A1/en not_active Abandoned
- 2012-04-16 EP EP12717246.8A patent/EP2699848B1/en active Active
- 2012-04-16 WO PCT/EP2012/056878 patent/WO2012143318A1/en active Application Filing
- 2012-04-16 CA CA2833464A patent/CA2833464A1/en not_active Abandoned
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE709065C (en) * | 1935-07-17 | 1941-08-07 | Rene Alexandre Arthur Couzinet | Feeding device for gas turbines |
JPS62118958U (en) * | 1986-01-16 | 1987-07-28 | ||
JPH1082527A (en) * | 1996-09-05 | 1998-03-31 | Toshiba Corp | Gas turbine combustor |
WO2011012126A2 (en) * | 2009-07-31 | 2011-02-03 | Man Diesel & Turbo Se | Gas turbine combustion chamber |
Also Published As
Publication number | Publication date |
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EP2699848A1 (en) | 2014-02-26 |
US20140144138A1 (en) | 2014-05-29 |
RU2544400C1 (en) | 2015-03-20 |
DE102011007562A1 (en) | 2012-10-18 |
CA2833464A1 (en) | 2012-10-26 |
EP2699848B1 (en) | 2015-06-10 |
JP5678232B2 (en) | 2015-02-25 |
WO2012143318A1 (en) | 2012-10-26 |
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