JPS599431A - Apparatus for supporting combustor of gas turbine - Google Patents
Apparatus for supporting combustor of gas turbineInfo
- Publication number
- JPS599431A JPS599431A JP11836682A JP11836682A JPS599431A JP S599431 A JPS599431 A JP S599431A JP 11836682 A JP11836682 A JP 11836682A JP 11836682 A JP11836682 A JP 11836682A JP S599431 A JPS599431 A JP S599431A
- Authority
- JP
- Japan
- Prior art keywords
- stopper
- groove
- liner
- combustor
- gas turbine
- 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
Classifications
-
- 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
- F23R3/60—Support structures; Attaching or mounting means
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
Description
【発明の詳細な説明】 本発明はガスタービン燃焼器の支持装置に関する。[Detailed description of the invention] The present invention relates to a support device for a gas turbine combustor.
ガスタービンの燃焼器は作動流体としての燃焼ガスを生
成し、このガスをタービン動翼部に導く役目をもってい
る。第１図は排ガス中のＮ０ｘｉを抑制できる低ＮＯｘ
型燃焼器の構成を示したものである。燃焼器１の主要構
成要素は、燃焼ガスを生成するライナ２とこの燃焼ガス
を動翼部に導く尾筒３及び燃料ノズル６からなシ、これ
らは外筒４及びカバー５によって密閉された高圧チャン
バー内に保持される。The combustor of a gas turbine has the role of generating combustion gas as a working fluid and guiding this gas to the turbine rotor blades. Figure 1 shows low NOx that can suppress NOxi in exhaust gas.
This figure shows the configuration of a type combustor. The main components of the combustor 1 include a liner 2 that generates combustion gas, a transition pipe 3 that guides the combustion gas to the rotor blades, and a fuel nozzle 6. held within the chamber.
低ＮＯｘ型燃焼器１の構造上の％徴はライナ２が副燃焼
室７と主燃焼室８に分けられていることにある。副燃焼
室７では空気と燃料とのミキシングをよくし、希釈燃焼
を行なわせる。すなわち、圧縮機９で加圧された空気は
ディフューザ部１゜を通シ、尾筒３の外面を冷却しなが
らライナ２と外筒４との環状部をライナ頭部側に向は逆
流する。A structural feature of the low NOx type combustor 1 is that the liner 2 is divided into an auxiliary combustion chamber 7 and a main combustion chamber 8. In the auxiliary combustion chamber 7, air and fuel are mixed well and diluted combustion is performed. That is, the air pressurized by the compressor 9 passes through the diffuser portion 1° and flows backward through the annular portion of the liner 2 and the outer cylinder 4 toward the liner head side while cooling the outer surface of the transition piece 3.
副燃焼室７はミキシングの増進を図るために流入する空
気に周方向の旋回をかける旋回器１１が付属する。さら
に、保炎性をよくシ、またガス体の滞留時間を短かくす
るために径が主燃焼室８よυも小さ目に作られている。The sub-combustion chamber 7 is attached with a swirler 11 that swirls the incoming air in the circumferential direction in order to improve mixing. Furthermore, in order to improve flame stability and shorten the residence time of the gas, the main combustion chamber 8 is made smaller in diameter.
一方、主燃焼室８は副燃焼部での未燃燃料を完全に燃焼
させると共に、希釈空気孔１２よシ流入した空気によシ
所定のガス温度にし、タービン部１１に燃焼ガスを供給
する。On the other hand, the main combustion chamber 8 completely burns the unburned fuel in the sub-combustion section, has a predetermined gas temperature with the air flowing in through the dilution air hole 12, and supplies combustion gas to the turbine section 11.
低ＮＯｘ化に伴い生ずる強度信頼性の問題点の一つに振
動がある。これは、希釈燃焼を実施することによって、
燃焼の安定性は低下し、いわゆる振動燃焼の振幅が増加
するために、燃焼器への振動応答の程度も太きくなシ、
特に、燃焼器の支持部を中心に損傷を受けやすくなって
きている。燃焼器に対する信頼性が特に強く求められる
理由は、支持部等が単に破損するという問題に終らず、
破損した物体は、はとんどの場合が燃焼器内に吸込まれ
、タービン回転翼に衝突して、重大な事故を発生させる
可能性を持っているためである。ところで、従来型燃焼
器ライナ部の支持はライナの前部と後部で行なわれ、前
部は第２図に詳細を示すようにＵ字型の市め金１３が１
２０度間隔に３個設けられ、外筒４の内面に溶接された
支持板１４に押込めることにより単純支持されている。One of the problems with strength reliability that arises with the reduction in NOx is vibration. This is done by carrying out diluted combustion.
Combustion stability decreases and the amplitude of so-called oscillatory combustion increases, so the degree of vibration response to the combustor also increases.
In particular, the supporting parts of the combustor are becoming more susceptible to damage. The reason why the reliability of the combustor is particularly strongly required is not limited to the problem of simple damage to the support parts, etc.
This is because, in most cases, the damaged object will be sucked into the combustor and collide with the turbine rotor, potentially causing a serious accident. By the way, support for the conventional combustor liner is carried out at the front and rear parts of the liner, and the front part has a U-shaped seal 13 as shown in detail in Figure 2.
Three pieces are provided at 20 degree intervals and simply supported by being pushed into a support plate 14 welded to the inner surface of the outer cylinder 4.
一方、ライナ２の後部は円弧状の板バネ１５がライナ周
上に配置されていて、この部分を尾筒３内に押し込める
ことによシ弾性支持される。On the other hand, the rear part of the liner 2 is elastically supported by an arcuate plate spring 15 arranged around the liner circumference and pushed into the transition piece 3.
ここでは、止め金部の支持法の問題点について述べる。Here, we will discuss the problems with the method of supporting the stopper part.
第１点は、止め金がＵ字形をしていて直接支持板１４と
接触する点にある。支持板１４は止め金１３の曲部１６
に接触して止め金にライナ軸方向の力をおよぼす。止め
金１３は底辺１７部でライナに溶接されているため、曲
部１６に力がかかると、この溶接部に応力が発生する。The first point is where the catch is U-shaped and directly contacts the support plate 14. The support plate 14 is connected to the curved portion 16 of the stopper 13.
and exerts a force in the liner axial direction on the stopper. Since the catch 13 is welded to the liner at the bottom 17, when force is applied to the curved portion 16, stress is generated in this weld.
最大応力は止め金の入口根元部１８で発生する。この部
分は止め金の先端部にあたり、構造的にも、応力の集中
が起シ易い所になっている。The maximum stress occurs at the inlet root 18 of the catch. This part corresponds to the tip of the stopper, and is a place where stress concentration is likely to occur structurally.
第２点は、止め金が３個になっている点である。The second point is that there are three clasps.
一応、構造の対称性を満たすように取付けられているが
、支持点の数が少ないことからランダムな振動荷重に対
して、支持点で均一に荷重を分配することが難かしぐ、
荷重分布の偏υが生じ易い。Although it is installed to satisfy the symmetry of the structure, due to the small number of support points, it is difficult to evenly distribute the load at the support points against random vibration loads.
Unbalanced load distribution υ is likely to occur.
第３点は、一番問題となる、安全保護対策である。すな
わち、万一、止め金部が破損した場合、燃焼器内に流れ
込む危険性をもつ。The third point is the most important one, security measures. That is, if the stopper part were to break, there is a risk that it would flow into the combustor.
本発明の目的は、ガスタービン燃焼器の支持部について
、振動に対する減衰効果を大きくし、かつ応力集中の小
ない構造とし、万一、破損しても取伺部から外に流出し
ない安全なガスタービン燃焼器の支持装置を提供するこ
とにある。It is an object of the present invention to provide a supporting part of a gas turbine combustor with a structure that has a large damping effect against vibrations and has a small stress concentration, so that even if it breaks, it will not leak out from the receiving part. An object of the present invention is to provide a support device for a turbine combustor.
燃焼器の支持部は特に応力の発生が太きくなるので、ま
ず１点は破損しないような構造を採用すること。２点目
は万一破損しても、その破損物が何処へも飛び出ないよ
うな構造にしておくことが必要である。まず、破損しな
い構造にするために採った方法は、支持部で振動エネル
ギを吸収できるようにバネによる弾性支持を゛採用して
いる。また、流出防止法については、ストッパを支持す
る相手方の部材が、ストッパを完全に包むように保持す
ることにより問題の解決を図った。The support part of the combustor is particularly prone to stress, so first of all, a structure must be adopted that will not cause damage. The second point is that even if something breaks, it needs to be structured so that the damaged item will not fly out anywhere. First, the method adopted to create a structure that will not break is to use elastic support using springs so that vibration energy can be absorbed by the support section. In addition, regarding the leakage prevention method, the problem was solved by holding the stopper so that the other member supporting the stopper completely surrounded the stopper.
以下、本発明の一実施例を第４図〜第１０図によ′り説
明する。An embodiment of the present invention will be described below with reference to FIGS. 4 to 10.
まず本発明の特徴の一つでちる破損部材の流出防止構造
について説明する。First, a structure for preventing leakage of damaged members, which is one of the features of the present invention, will be explained.
本発明では燃焼器前部のストッパ１９は９０度間隔に４
個つけられる。ストッパ１９は後述するように、箱形と
なり、その底辺の４辺がライナ２の前端に近いところに
溶接される。４本のストッパは全く同一条件で支持され
る。一方、相手方の支持部材２０け、外筒４の内面に一
端が溶接された板状のブロックである。第６図、第７図
に詳細に示すように、このブロックにはストッパの幅、
奥行よりも幾分広い溝部２４．２４が設けられている。In the present invention, the stoppers 19 at the front of the combustor are arranged at four intervals of 90 degrees.
Can be attached individually. As will be described later, the stopper 19 has a box shape, and its four bottom sides are welded near the front end of the liner 2. The four stoppers are supported under exactly the same conditions. On the other hand, the other support member 20 is a plate-shaped block with one end welded to the inner surface of the outer cylinder 4. As shown in detail in Figures 6 and 7, this block has the width of the stopper,
A groove portion 24.24 is provided which is somewhat wider than its depth.
この溝部は支持部材２０の長手方向の途中まで設けられ
ていてストッパがライナの長手方向へ変形する場合、止
め金の役目をする。This groove is provided part way in the longitudinal direction of the support member 20, and serves as a stop when the stopper is deformed in the longitudinal direction of the liner.
従って、ライナ２を糾込む場合は、４本のストッパがこ
の溝部２４に入るよう押し込められる。Therefore, when tightening the liner 2, the four stoppers are pushed into the groove 24.
この状態でカバー５が外筒に締結される。ところで、カ
バー５には第８図に示すように、ちょうどストッパと合
い対する点に支持部材２０に切られた溝よシも幅、高さ
共、幾分大きめのブロック２１が設けられている。カバ
ー５が外筒４に締結された状態ではこのブロック２１の
先端がちょうど支持部材２０の前面２５に接する程度の
寸法にできている。このように本ライナのストッパは支
持部材２０及びブロック２１によって周囲を完全に包み
込まれた状態に支持されるため、仮に、ストッパ部が根
元から折れた場合でも外に抜は出す支配はない。In this state, the cover 5 is fastened to the outer cylinder. By the way, as shown in FIG. 8, the cover 5 is provided with a block 21 which is somewhat larger in both width and height than the groove cut in the support member 20 at the point where it meets the stopper. When the cover 5 is fastened to the outer cylinder 4, the tip of the block 21 is dimensioned to just touch the front surface 25 of the support member 20. In this way, the stopper of this liner is supported in a state where it is completely surrounded by the supporting member 20 and the block 21, so even if the stopper part were to break from the base, there would be no way for it to come out.
次に、本発明のもう一つの特徴である振動力の吸収構造
について四明する。Next, the vibration force absorption structure, which is another feature of the present invention, will be explained in detail.
燃焼器は振動燃焼によって励振を受は振れるが燃焼器頭
部での振れの大きさはライナの半径方向と軸方向が特に
大きいことが測定の結果知られている。そこで、これら
の方向の振動に対して、できるだけその力を弱めるため
に採られたのが本構造である。本構造ではこの振動力に
対する影響を軟らげるために、板バネによって対処して
いる。Although the combustor receives excitation due to oscillatory combustion, it is known from measurements that the magnitude of the vibration at the head of the combustor is particularly large in the radial and axial directions of the liner. Therefore, this structure was adopted to weaken the vibration force as much as possible against vibrations in these directions. In this structure, a leaf spring is used to soften the influence of this vibration force.
すなわち、第６図、第７図に示されるようＫ、ライナ半
径方向の振動に対しては支持部材２０内に保持された円
弧状の板バネ２７によって行なう。That is, as shown in FIGS. 6 and 7, vibrations in the radial direction of the liner are handled by an arc-shaped leaf spring 27 held within the support member 20.
この板バネ２７は、板バネ固定部材２６に、ライナ中心
部に向って凸形（円弧形）となるように両端部が支持さ
れている。一方、支持部材２０は、この板バネ固定部材
２７を挿入できるように横溝２２が設けられている。ス
トッパ１９を押し込んだ状態では、板バネ２７と、スト
ッパ上面２８が弾性状態で支持されることになる。板バ
ネ固定部材２６はまた振動を吸収する役目も負っている
。Both ends of the leaf spring 27 are supported by the leaf spring fixing member 26 so as to have a convex shape (arc shape) toward the center of the liner. On the other hand, the support member 20 is provided with a lateral groove 22 so that the plate spring fixing member 27 can be inserted therein. When the stopper 19 is pushed in, the leaf spring 27 and the top surface 28 of the stopper are supported in an elastic state. The leaf spring fixing member 26 also has the role of absorbing vibrations.
すなわち、２６の上面２９と横溝２３の面３０が面接触
した状態にあるが、この２面は軸方向には相対的な変形
ができるようになっていて摩擦による振動エネルギを吸
収できる構造である。That is, the upper surface 29 of the lateral groove 26 and the surface 30 of the lateral groove 23 are in surface contact, but these two surfaces can be deformed relative to each other in the axial direction, so that the structure is such that vibration energy due to friction can be absorbed. .
一方、ライナ軸方向の振動吸収には、やけシ板バネが用
いられるが、板バネを支持部材に設けるのけ構造的に困
難であるので、この方向についてはストッパ部にバネ板
を取シ付けである。第９図。On the other hand, a thin plate spring is used to absorb vibration in the liner axial direction, but it is structurally difficult to install a plate spring on the support member, so in this direction, a spring plate is attached to the stopper part. It is. Figure 9.
第１０図にその取付状況を示す。まず、本ストツパハ箱
形のストッパになっていてその底辺の４辺がライナ２に
溶接される。このような固定方法は、特に応力の集中を
平均化することができ強度上有利でおる。さて、円弧状
板バネは第１０図のようにストッパ１９の高さ方向全面
をおおうように両端でスポット溶接されて固定される。Figure 10 shows the installation situation. First, this stopper is a box-shaped stopper whose four bottom sides are welded to the liner 2. Such a fixing method is particularly advantageous in terms of strength because it can even out stress concentration. Now, as shown in FIG. 10, the arcuate leaf spring is fixed by spot welding at both ends so as to cover the entire surface of the stopper 19 in the height direction.
ライナが組込まれた状態では第７図に示すように、円弧
状板バネ３１は、支持部材２０の側面２５と接触し弾性
支持された状態にある。When the liner is installed, the arcuate leaf spring 31 is in contact with the side surface 25 of the support member 20 and is elastically supported, as shown in FIG.
このように本発明によれば、強度的にも強化が図られ、
しかも、安全保護機構を有する信頼性の高い燃焼支持構
造を提供することができる。As described above, according to the present invention, the strength is also strengthened,
Moreover, a highly reliable combustion support structure having a safety protection mechanism can be provided.
第１図はガスタービン燃焼器の概略図、第２図は従来の
燃焼器支持部の斜視図、第３図は第２図におけるストッ
パと支持部材の組込状況を示す説明図、第４図乃至第１
０図は本発明の一実施例で（９）
あるガスタービン燃焼器の支持装置を示すものであシ、
第４図は燃焼器の周方向断面図、第５図は燃焼器の軸方
向断面図、第６図は支持部の詳細を示す周方向断面図、
第７図は支持部の詳細を示す軸方向断面図、第８図はカ
バ一部断面図、第９図はストッパの取付状況を示す斜視
図、第１０図はストッパ部の拡大図である。
１・・・燃焼器、２・・・ライナ、３・・・尾筒、４・
・・外筒、５・・・カバー、６・・・燃料ノズル、７・
・・副燃焼室、８・・・主燃焼室、９・・・圧縮機、１
０・・・ディフューザ、１１・、・タービン、１２・・
・希釈空気孔、１３・・・止め金、１４・・・支持板、
１５・・・スプリングシール、１６・・・曲部、１７・
・・底辺、１１Ａ・・・入口根元部、１９・・・ストッ
パ、２０・・・支持部材、２１・・・ブロック、２２・
・・横溝、２３・・・溝部、２４・・・前面、２６・・
・板バネ固定部材、２７・・・板バネ、２８・・・スト
ッパ上面、２９・・・上面、３０・・・面、３１・・・
円弧状板ン（１０）
第１図
％５図Fig. 1 is a schematic diagram of a gas turbine combustor, Fig. 2 is a perspective view of a conventional combustor support section, Fig. 3 is an explanatory diagram showing how the stopper and support member in Fig. 2 are assembled, and Fig. 4 to the first
Figure 0 is an embodiment of the present invention (9) and shows a support device for a certain gas turbine combustor.
FIG. 4 is a circumferential sectional view of the combustor, FIG. 5 is an axial sectional view of the combustor, and FIG. 6 is a circumferential sectional view showing details of the support part.
FIG. 7 is an axial sectional view showing details of the support part, FIG. 8 is a partial sectional view of the cover, FIG. 9 is a perspective view showing how the stopper is attached, and FIG. 10 is an enlarged view of the stopper part. 1... Combustor, 2... Liner, 3... Transition piece, 4...
・・Outer cylinder, 5・Cover, 6・Fuel nozzle, 7・
... Sub-combustion chamber, 8... Main combustion chamber, 9... Compressor, 1
0... Diffuser, 11... Turbine, 12...
・Dilution air hole, 13...stopper plate, 14...support plate,
15... Spring seal, 16... Curved portion, 17.
...Base, 11A...Inlet base, 19...Stopper, 20...Support member, 21...Block, 22...
...Horizontal groove, 23...Groove, 24...Front surface, 26...
- Leaf spring fixing member, 27... Leaf spring, 28... Stopper top surface, 29... Top surface, 30... Surface, 31...
Arc-shaped plate (10) Figure 1 Figure %5
Claims (1)
隔に設けた４個の箱型ストッパよ多構成し、該ストッパ
は燃焼器を格納する外筒の内面に取付けられた支持部材
の溝部に挿入され、溝部の入口部は外筒の前ぶたに取付
けられた４個の突起部により閉塞され、ストッパが溝部
から抜は出さないように組込まれることを特徴とするガ
スタービン燃焼器の支持装置。 ２、特許請求の範囲第１項において、支持部材の溝部の
上面には円弧状の板バネが設置された支持板が挿入され
ておシ、該板バネと箱形ストッパはストッパの上面部で
接触し、弾性支持されることを特徴とするガスタービン
燃焼器の支持装置。 ３、特許請求の範囲第１項において、箱形ストッパは、
前後面、側面、及び上面を有し、底辺の４辺がライナに
溶接され固定されるストッパの後面には円弧状の板バネ
がストッパの高さ方向に溶接されて、該板バネは支持部
材の溝部に挿入された際、溝部の面と弾性接触するよう
に配置されることを特徴とするガスタービン燃焼器の支
持装置。[Claims] 1. The front support part of the gas turbine combustor liner is configured with four box-shaped stoppers arranged at 90-degree intervals, and the stoppers are attached to the inner surface of the outer cylinder housing the combustor. The stopper is inserted into the groove of the supporting member, the entrance of the groove is closed by four protrusions attached to the front lid of the outer cylinder, and the stopper is incorporated so as not to be removed from the groove. Support device for gas turbine combustor. 2. In claim 1, a support plate on which an arcuate leaf spring is installed is inserted into the upper surface of the groove of the support member, and the leaf spring and the box-shaped stopper are connected to the upper surface of the stopper. A support device for a gas turbine combustor, characterized in that it is in contact and elastically supported. 3. In claim 1, the box-shaped stopper is
An arc-shaped plate spring is welded to the rear surface of the stopper, which has front and rear surfaces, side surfaces, and a top surface, and whose four bottom sides are welded and fixed to the liner in the height direction of the stopper, and the plate spring serves as a support member. A support device for a gas turbine combustor, characterized in that the support device is arranged so as to come into elastic contact with a surface of the groove when inserted into the groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11836682A JPS599431A (en) | 1982-07-09 | 1982-07-09 | Apparatus for supporting combustor of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11836682A JPS599431A (en) | 1982-07-09 | 1982-07-09 | Apparatus for supporting combustor of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS599431A true JPS599431A (en) | 1984-01-18 |
Family
ID=14734925
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP11836682A Pending JPS599431A (en) | 1982-07-09 | 1982-07-09 | Apparatus for supporting combustor of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS599431A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2639095A1 (en) * | 1988-11-17 | 1990-05-18 | Snecma | TURBOMACHINE COMBUSTION CHAMBER WITH FLOATING MOUNT PREVAPORIZATION BOWLS |
| JPH05118549A (en) * | 1991-10-25 | 1993-05-14 | Nissan Motor Co Ltd | Burner for gas turbine |
| JP2009047409A (en) * | 2007-08-14 | 2009-03-05 | General Electric Co <Ge> | Combustion liner stopper in gas turbine |
| JP2012013076A (en) * | 2010-06-29 | 2012-01-19 | Nuovo Pignone Spa | Liner aft end support mechanisms and spring loaded liner stop mechanisms |
| CN102434892A (en) * | 2010-08-10 | 2012-05-02 | 通用电气公司 | Combustion liner stop blocks having insertable wear features and related methods |
| CN102798150A (en) * | 2011-05-24 | 2012-11-28 | 通用电气公司 | System and method for flow control in gas turbine engine |
| CN102798148A (en) * | 2011-05-24 | 2012-11-28 | 通用电气公司 | System and method for turbine combustor mounting assembly |
| CN106247401A (en) * | 2015-06-15 | 2016-12-21 | 安萨尔多能源英国知识产权有限公司 | The damping unit of parts and the method for the described damping unit of assembling in turbine |
| EP2325564A3 (en) * | 2009-11-23 | 2017-12-27 | Rolls-Royce plc | Combustor system |
| EP3457031A1 (en) * | 2017-09-18 | 2019-03-20 | Doosan Heavy Industries & Construction Co., Ltd | Combustor and gas turbine including the same |
| FR3081494A1 (en) * | 2018-05-28 | 2019-11-29 | Safran Aircraft Engines | GAS TURBOMACHINE COMBUSTION MODULE WITH BOTTOM BOTTOM |
-
1982
- 1982-07-09 JP JP11836682A patent/JPS599431A/en active Pending
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2639095A1 (en) * | 1988-11-17 | 1990-05-18 | Snecma | TURBOMACHINE COMBUSTION CHAMBER WITH FLOATING MOUNT PREVAPORIZATION BOWLS |
| JPH05118549A (en) * | 1991-10-25 | 1993-05-14 | Nissan Motor Co Ltd | Burner for gas turbine |
| JP2009047409A (en) * | 2007-08-14 | 2009-03-05 | General Electric Co <Ge> | Combustion liner stopper in gas turbine |
| DE102008002981B4 (en) * | 2007-08-14 | 2021-07-01 | General Electric Co. | Combustion chamber insert stop in a gas turbine |
| EP2325564A3 (en) * | 2009-11-23 | 2017-12-27 | Rolls-Royce plc | Combustor system |
| JP2012013076A (en) * | 2010-06-29 | 2012-01-19 | Nuovo Pignone Spa | Liner aft end support mechanisms and spring loaded liner stop mechanisms |
| CN102434892A (en) * | 2010-08-10 | 2012-05-02 | 通用电气公司 | Combustion liner stop blocks having insertable wear features and related methods |
| CN102798148B (en) * | 2011-05-24 | 2016-08-10 | 通用电气公司 | System and method for turbine combustion chamber mounting assembly |
| EP2527741A3 (en) * | 2011-05-24 | 2013-09-18 | General Electric Company | System and method for flow control in gas turbine engine |
| US8925326B2 (en) | 2011-05-24 | 2015-01-06 | General Electric Company | System and method for turbine combustor mounting assembly |
| EP2527744A3 (en) * | 2011-05-24 | 2013-04-17 | General Electric Company | System and method for turbine combustor mounting assembly |
| CN102798148A (en) * | 2011-05-24 | 2012-11-28 | 通用电气公司 | System and method for turbine combustor mounting assembly |
| CN102798150A (en) * | 2011-05-24 | 2012-11-28 | 通用电气公司 | System and method for flow control in gas turbine engine |
| CN106247401A (en) * | 2015-06-15 | 2016-12-21 | 安萨尔多能源英国知识产权有限公司 | The damping unit of parts and the method for the described damping unit of assembling in turbine |
| CN106247401B (en) * | 2015-06-15 | 2020-08-28 | 安萨尔多能源英国知识产权有限公司 | Damping device for components in a turbomachine and method for assembling said damping device |
| EP3457031A1 (en) * | 2017-09-18 | 2019-03-20 | Doosan Heavy Industries & Construction Co., Ltd | Combustor and gas turbine including the same |
| US10982854B2 (en) | 2017-09-18 | 2021-04-20 | Doosan Heavy Industries & Construction Co., Ltd. | Combustor and gas turbine including the same |
| FR3081494A1 (en) * | 2018-05-28 | 2019-11-29 | Safran Aircraft Engines | GAS TURBOMACHINE COMBUSTION MODULE WITH BOTTOM BOTTOM |
| EP3575689A1 (en) * | 2018-05-28 | 2019-12-04 | Safran Aircraft Engines | Gas turbine engine combustion module with chamber bottom abutment |
| US11725822B2 (en) | 2018-05-28 | 2023-08-15 | Safran Aircraft Engines | Combustion module for a gas turbo engine with chamber bottom stop |
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