JP2001509874A - Gas turbine equipment with combustion chamber lined with ceramic blocks - Google Patents

Gas turbine equipment with combustion chamber lined with ceramic blocks

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Publication number
JP2001509874A
JP2001509874A JP53245998A JP53245998A JP2001509874A JP 2001509874 A JP2001509874 A JP 2001509874A JP 53245998 A JP53245998 A JP 53245998A JP 53245998 A JP53245998 A JP 53245998A JP 2001509874 A JP2001509874 A JP 2001509874A
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Prior art keywords
ceramic
layer
gas turbine
combustion chamber
ceramic block
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JP53245998A
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JP4294736B2 (en
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ナイデル、アンドレアス
ラシュケ、クラウス
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Siemens AG
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Siemens AG
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Ceramic Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Solid-Fuel Combustion (AREA)

Abstract

(57)【要約】 圧縮機とタービンとの間に中実のセラミックブロック（１０）で内張りされた燃焼室（７）が配置され、ロータ（２）に動翼（５、６）が、このロータ（２）を包囲する車室（１）に静翼（３、４）がそれぞれ取り付けられ、特に少なくとも第１段のタービン翼列（３、５）がセラミック断熱層を有しているガスタービン設備において、本発明に基づいて、セラミックブロック（１０）のセラミック層の「剥げ落ち」およびこれに伴うタービン翼の断熱層の破損を防止するために、セラミックブロック（１０）が表面に被覆層（１２、１３）を備えている。   (57) [Summary] A combustion chamber (7) lined with a solid ceramic block (10) is arranged between the compressor and the turbine, and rotor blades (5, 6) surround the rotor (2). The present invention is particularly applicable to a gas turbine facility in which stationary vanes (3, 4) are attached to a cabin (1) to be mounted, and at least the first stage turbine cascade (3, 5) has a ceramic heat insulating layer. Based on this, the ceramic block (10) is provided with a coating layer (12, 13) on the surface in order to prevent the "peeling off" of the ceramic layer of the ceramic block (10) and the consequent damage of the thermal insulation layer of the turbine blade. ing.

Description

【発明の詳細な説明】 燃焼室がセラミックブロックで内張りされているガスタービン設備 本発明は、中実のセラミックブロックで内張りされた燃焼室、動翼が固定され たロータおよび静翼が固定された車室を備え、特に少なくとも第１段のタービン 翼がセラミック断熱層を有しているガスタービン設備に関する。 この種のガスタービンは、例えばドイツ特許出願公開第４３４３３１９号明細 書で知られている。非常に高い入口温度を実現するために、最新のガスタービン において燃焼室、特にその炎筒は熱的に極端に大きく負荷できるように形成され ている。この目的のために、燃焼室の内壁はセラミック断熱層で覆われるか、あ るいは中実のセラミックブロックからなるシールドが設けられる。 これに加えて、ガスタービン設備のタービン翼、特に燃焼室に隣接する第１段 のタービン翼には、しばしば熱保護層としてセラミック断熱層が設けられている 。このセラミック断熱層は、例えば酸化イットリウム安定化酸化ジルコニウム層 から成っている。 実験の結果、燃焼室の内張りに中実のセラミックブロックを利用する場合、敏 感なセラミック断熱層を備えたタービン翼との関連において、このセラミック断 熱層がひどい機械的摩耗を受けることが確認されている。 本発明の課題は、冒頭に述べた形式のガスタービン設備において、一方では燃 焼室およびタービン翼を熱的過負荷から保護し、他方ではタービン翼の寿命を長 くすることができるような処置を講ずることにある。 この課題は本発明に基づいて、セラミックブロックが表面に被覆層を備えてい ることによって解決される。 セラミックブロックは他の材料、例えば耐熱合金から成る断熱板よりも高い材 料温度にすることができ、且つ許容されるという利点を有する。またセラミック ブロックの固定要素を冷却するだけでよい。この結果、例えば高い許容材料温度 のために、燃焼室内張りの表面に到達する不完全燃焼粒子はそこで完全燃焼し、 これによって排気ガス中における有毒な一酸化炭素（ＣＯ）が無害な二酸化炭素 （ＣＯ２）に変換されるために少量となる。その上に、金属内張りに比べて必要 な冷却空気量が少量となり、その分の空気は燃焼用に利用できる。これによって 火炎温度が低下し、環境を汚染する窒素酸化物の発生量が著しく減少する。従っ て効率上並びに環境上の理由から中実のセラミックブロックによって燃焼室を内 張りすることが有利である。しかしこのようなセラミックブロックを利用する場 合、その表面から粒子が剥がれ落ち、この粒子が燃焼ガス流とタービン翼との大 きな相対速度のために弾丸のようにタービン翼に衝突し、激しい摩耗作用を生ず るという問題がある。 セラミックブロックを本発明に基づいて被覆することによって、セラミックブ ロックの表面からのそのような粒子の剥げ落ちは有効に防止される。この場合特 に、セラミックブロックが燃焼室壁に取り付けられる前に、これを被覆すること が有利である。この被覆はそのために、熱的な繰り返し負荷の際における剥げ落 ちを防止するために、セラミックブロックへの良好な接着および被覆層の良好な 結合が保証されるように実施しなければならない。これによってセラミックブロ ックの被覆層は表面粒子を固定するための層を形成する。従って、燃焼室内張り として中実のセラミックブロックをタービン翼におけるセラミック断熱層と組み 合わせて利用することができる。 本発明の実施形態において、被覆層は金属材料から成り、特に真空プラズマス プレイ（ＶＰＳ）法によって設けられる。 このためにＶＰＳ法で種々に形成できる腐食保護層を利用することができ、例 えばＭＣｒＡｌＹ（ここでＭはＮｉあるいはＣｏである）を利用することができ る。 セラミックカバー層と、接着剤としての金属ボンドコート(Bondcoat)とから成 る複合被覆層を採用することもできる。そのセラミックカバー層は、有利にはエ アプラズマスプレイ（ＡＰＳ）法によって設けられる。 ＶＰＳ・ボンドコートを設けることなく、セラミック層でセラミックブロック を直接被覆することも考えられる。 セラミックブロックとセラミックＡＰＳ・被覆層との熱膨張係数の僅かな差が 熱的繰り返し負荷に対する強度に有効に作用する。断熱層としてセラミック層を 利用することにより、燃焼室内張りを冷却するために必要な冷却空気量が一層減 少されるという追加的な利点が得られる。そのセラミック層として、例えばＹ2 Ｏ3安定化ＺｒＯ2のような通常の断熱層あるいはまたＳｉＯ2ないしＡｌ2Ｏ3が 考えられる。 本発明においてまた、セラミックカバー層がエアプラズマスプレイ（ＡＰＳ） 法によって設けられることが有利である。 ＡＰＳ法はＶＰＳ法に比べてコスト的に有利である。 特にセラミックブロックを多層構造で被覆することも、熱的な観点あるいは被 覆層の良好な結合の観点から有利である。 全般的に接着層並びにその外側の層は、熱膨張挙動および化学的組成が層の厚 さに関して連続的に変化するような段階層として形成される。 以下図に示した実施例を参照して本発明を詳細に説明する。 図１はガスタービン設備の部分概略縦断面図、 図２は被覆層を明瞭にするために歪曲して拡大して描いた燃焼室壁の部分横断 面図である。 図１には本発明に基づくガスタービン設備が縦断面図で示されている。このガ スタービン設備は車室１とロータ２とを備え、この車室１には静翼３、４が、ロ ータ２には動翼５、６がそれぞれ固定されている。燃焼室７にバーナ１４、１５ を介して燃料が注入され、この燃料は圧縮機１６からの空気で燃焼される。この 圧縮機１６はガスタービン設備の入口部分として示されている。流入空気（矢印 １７、１８）は燃焼室７に流入する前に、この入口部分内において圧縮される。 燃焼ガスの膨張がタービンを駆動する働きをする。電気エネルギを発生するた めに、タービンロータに接続された連結軸１９によって発電機２０が駆動される 。 図２には環状燃焼室の表面部位が拡大横断面図で示されている。例えば金属か ら成る燃焼室壁１１に、セラミックブロック１０が固定要素８、９によって固定 されている。このセラミックブロック１０は、例えば酸化けい素あるいは酸化ア ルミニウムから成っている。 図２にはセラミックブロック１０の二つの層から成る被覆層が拡大して示され ている。その下側層は接着層（ボンドコート）１２であり、上側層はこの上側層 １２に特に良好に付着するセラミック層１３である。これらの下側層１２および 上側層１３は一緒に、セラミックブロック１０を覆い、このセラミックブロック １０の表面から剥げ落ちる粒子を結合する固い層を形成している。これによって そのような粒子が車室あるいはまたロータにあるタービン翼の断熱層に侵食作用 を与えることはなくなる。その接着剤層１２は、好適には金属・クロム・アルミ ニウム・イットリウム・合金（ＭＣｒＡｌＹ）から成り、断熱層１３は好適には 酸化イットリウム安定化酸化ジルコニウム、ＳｉＯ2あるいはＡｌ2Ｏ3から成っ ている。 図２には範囲２１に例えばセラミックブロックの単一被覆層２２が示されてい る。この被覆層はセラミックスから成っている。DETAILED DESCRIPTION OF THE INVENTION       Gas turbine equipment with combustion chamber lined with ceramic blocks   The present invention provides a combustion chamber lined with solid ceramic blocks, With a fixed rotor and stationary vanes, in particular at least a first stage turbine The present invention relates to a gas turbine facility in which a blade has a ceramic heat insulating layer.   A gas turbine of this kind is described, for example, in DE-A 43 43 319. Known in the book. State-of-the-art gas turbines to achieve very high inlet temperatures The combustion chamber, especially its flame tube, is formed so that it can be extremely thermally loaded. ing. For this purpose, the inner walls of the combustion chamber are covered with a ceramic insulation layer or Alternatively, a shield made of a solid ceramic block is provided.   In addition to this, the turbine blades of the gas turbine installation, especially the first stage adjacent to the combustion chamber Turbine blades are often provided with a ceramic insulation layer as a thermal protection layer . This ceramic insulation layer may be, for example, a yttrium oxide stabilized zirconium oxide layer. Consists of   As a result of experiments, when using a solid ceramic block for the lining of the combustion chamber, In the context of turbine blades with a sensitive ceramic thermal barrier, It has been found that the thermal layer undergoes severe mechanical wear.   The object of the present invention is to provide a gas turbine system of the type Protects the firing chamber and turbine blades from thermal overload, while extending the life of the turbine blades To take steps that can make it worse.   This object is achieved according to the invention in that the ceramic block has a coating layer on the surface. It is solved by doing.   Ceramic blocks are higher than other materials, for example, heat-insulating plates made of heat-resistant alloys. It has the advantage that the feed temperature can be kept and is acceptable. Also ceramic It is only necessary to cool the fixed elements of the block. As a result, for example, a high allowable material temperature Due to the incompletely burned particles reaching the surface of the combustion chamber lining, they burn completely there, This reduces toxic carbon monoxide (CO) in the exhaust gas to harmless carbon dioxide It becomes a small amount because it is converted to (CO2). On top of that, it is necessary compared to metal lining The required amount of cooling air becomes small, and the air can be used for combustion. by this The flame temperature is reduced and the amount of nitrogen oxides polluting the environment is significantly reduced. Follow The combustion chamber is enclosed by a solid ceramic block for efficiency and environmental reasons. Tensioning is advantageous. However, when using such a ceramic block, In this case, particles are peeled off from the surface, and the particles form a large part between the combustion gas flow and the turbine blade. Impacts the turbine blades like a bullet due to the relative velocity Problem.   By coating the ceramic block according to the invention, the ceramic block is The shedding of such particles from the surface of the lock is effectively prevented. In this case, Before the ceramic block is attached to the combustion chamber wall, Is advantageous. This coating is therefore subject to flaking during thermal cyclic loading. Good adhesion to the ceramic block and good coating layer to prevent Must be performed so that the coupling is guaranteed. This allows the ceramic block The coating layer of the pack forms a layer for fixing the surface particles. Therefore, the combustion chamber lining A solid ceramic block as a ceramic insulation layer in a turbine blade Can be used together.   In an embodiment of the invention, the coating layer is made of a metallic material, in particular a vacuum plasma It is provided by a play (VPS) method.   For this purpose, a corrosion protection layer that can be variously formed by the VPS method can be used. For example, MCrAlY (where M is Ni or Co) can be used. You.   It consists of a ceramic cover layer and a metal bond coat (Bondcoat) as an adhesive. A composite coating layer can also be employed. The ceramic cover layer is advantageously It is provided by a plasma spray (APS) method.   Ceramic block with ceramic layer without VPS / bond coat It is also conceivable to coat directly.   The slight difference in the coefficient of thermal expansion between the ceramic block and the ceramic APS / coating layer Effectively affects the strength against repeated thermal loads. Ceramic layer as heat insulation layer Utilization reduces the amount of cooling air required to cool the combustion chamber lining. The additional advantage of being reduced is obtained. As the ceramic layer, for example, YTwo OThreeStabilized ZrOTwoOrdinary heat-insulating layer such asTwoOr AlTwoOThreeBut Conceivable.   In the present invention, the ceramic cover layer may be an air plasma spray (APS). Advantageously, it is provided by a method.   The APS method is more cost effective than the VPS method.   In particular, coating the ceramic block with a multilayer structure is not possible from a thermal point of view or coating. It is advantageous in terms of good bonding of the overlayer.   In general, the adhesive layer and its outer layer have thermal expansion behavior and chemical composition It is formed as a graded layer that changes continuously with respect to its height.   Hereinafter, the present invention will be described in detail with reference to embodiments shown in the drawings.   FIG. 1 is a partial schematic longitudinal sectional view of a gas turbine facility,   Figure 2 shows a section across the combustion chamber wall, distorted and enlarged for clarity of the coating. FIG.   FIG. 1 shows a gas turbine installation according to the invention in longitudinal section. This mo The turbine apparatus includes a casing 1 and a rotor 2. The rotors 5 and 6 are fixed to the rotor 2 respectively. Burners 14, 15 in combustion chamber 7 , And is burned with air from the compressor 16. this The compressor 16 is shown as an inlet section of a gas turbine facility. Inflow air (arrow 17, 18) are compressed in this inlet section before flowing into the combustion chamber 7.   The expansion of the combustion gases serves to drive the turbine. To generate electrical energy For this purpose, the generator 20 is driven by the connecting shaft 19 connected to the turbine rotor. .   FIG. 2 shows an enlarged cross-sectional view of the surface portion of the annular combustion chamber. For example, metal The ceramic block 10 is fixed to the combustion chamber wall 11 by the fixing elements 8 and 9. Have been. The ceramic block 10 is made of, for example, silicon oxide or oxide oxide. Made of Luminium.   FIG. 2 shows a two-layer coating of the ceramic block 10 on an enlarged scale. ing. The lower layer is an adhesive layer (bond coat) 12, and the upper layer is the upper layer. 12 is a ceramic layer 13 which adheres particularly well. These lower layers 12 and The upper layer 13 together covers the ceramic block 10, 10 form a hard layer that binds the particles that flake off from the surface. by this Such particles can erode the thermal insulation of the turbine blades in the cabin or also in the rotor Will not be given. The adhesive layer 12 is preferably made of metal, chromium, aluminum, The heat insulating layer 13 is made of an alloy of nickel, yttrium and alloy (MCrAlY). Yttrium oxide stabilized zirconium oxide, SiOTwoOr AlTwoOThreeConsists of ing.   FIG. 2 shows a single covering layer 22 of, for example, a ceramic block in an area 21. You. This coating layer is made of ceramics.

Claims (1)

【特許請求の範囲】 １．中実のセラミックブロック（１０）で内張りされた燃焼室（７）、動翼（５ 、６）が固定されたロータ（２）および静翼（３、４）が固定された車室（１） を備え、特に少なくとも第１段のタービン翼がセラミック断熱層を有しているガ スタービン設備において、セラミックブロック（１０）が表面に被覆層（１２、 １３）を備えていることを特徴とするガスタービン設備。 ２．被覆層（１２、１３）が金属材料から成り、真空プラズマスプレイ（ＶＰＳ ）法によって設けられることを特徴とする請求項１記載のガスタービン設備。 ３．被覆層がボンドコートとセラミックカバー層とから成り、セラミックカバー 層（１３）がエアプラズマスプレイ（ＡＰＳ）法によって設けられることを特徴 とする請求項２記載のガスタービン設備。 ４．被覆層がセラミック層として形成されていることを特徴とする請求項１ない し３のいずれか１つに記載のガスタービン設備。 ５．セラミックブロック（１０）が多層構造をしていることを特徴とする請求項 １ないし４のいずれか１つに記載のガスタービン設備。[Claims] 1. Combustion chamber (7) lined with solid ceramic block (10), bucket (5 , 6) fixed to the rotor (2) and stationary vanes (3, 4) to the vehicle compartment (1) Wherein at least the first stage turbine blades have a ceramic insulation layer. In the turbine plant, a ceramic block (10) is provided with a coating layer (12, 13) A gas turbine facility comprising: 2. The coating layers (12, 13) are made of a metal material, and are formed by vacuum plasma spray (VPS). The gas turbine equipment according to claim 1, wherein the gas turbine equipment is provided by a method. 3. The coating layer comprises a bond coat and a ceramic cover layer, and the ceramic cover The layer (13) is provided by an air plasma spray (APS) method. The gas turbine equipment according to claim 2, wherein 4. 2. The method according to claim 1, wherein the coating layer is formed as a ceramic layer. The gas turbine equipment according to any one of Items 3 to 3. 5. 2. The ceramic block according to claim 1, wherein the ceramic block has a multilayer structure. The gas turbine equipment according to any one of 1 to 4.
JP53245998A 1997-01-29 1998-01-29 Gas turbine equipment with combustion chamber lined with ceramic blocks Expired - Lifetime JP4294736B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19704976A DE19704976C2 (en) 1997-01-29 1997-01-29 Gas turbine system with a combustion chamber casing lined with ceramic stones
DE19704976.1 1997-01-29
PCT/DE1998/000324 WO1998034068A1 (en) 1997-01-29 1998-01-29 Gas turbine installation with a ceramic-covered combustion chamber housing

Publications (2)

Publication Number Publication Date
JP2001509874A true JP2001509874A (en) 2001-07-24
JP4294736B2 JP4294736B2 (en) 2009-07-15

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EP (1) EP0960308B1 (en)
JP (1) JP4294736B2 (en)
DE (2) DE19704976C2 (en)
RU (1) RU2178530C2 (en)
UA (1) UA41485C2 (en)
WO (1) WO1998034068A1 (en)

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DE59802328D1 (en) 2002-01-17
WO1998034068A1 (en) 1998-08-06
EP0960308B1 (en) 2001-12-05
DE19704976C2 (en) 1999-02-25
EP0960308A1 (en) 1999-12-01
UA41485C2 (en) 2001-09-17
JP4294736B2 (en) 2009-07-15
DE19704976A1 (en) 1998-07-30
RU2178530C2 (en) 2002-01-20

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