JP2003185140A - Gas turbine combustor - Google Patents
Gas turbine combustorInfo
- Publication number
- JP2003185140A JP2003185140A JP2001391062A JP2001391062A JP2003185140A JP 2003185140 A JP2003185140 A JP 2003185140A JP 2001391062 A JP2001391062 A JP 2001391062A JP 2001391062 A JP2001391062 A JP 2001391062A JP 2003185140 A JP2003185140 A JP 2003185140A
- Authority
- JP
- Japan
- Prior art keywords
- gas turbine
- wear
- transition piece
- seal
- coating
- 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
Links
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、火力発電用ガスタ
ービンのトランジションピース（尾筒）の摩耗損傷を防
止したガスタービン燃焼器に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine combustor in which a transition piece (tail pipe) of a gas turbine for thermal power generation is prevented from being worn and damaged.
【０００２】[0002]
【従来の技術】近年、コンバインド発電システムなどの
火力発電プラントで用いられるガスタービンは、燃焼ガ
ス温度が１３００〜１５００℃と上昇していることか
ら、耐熱性に優れたガスタービン材料の開発が数多く行
われている。2. Description of the Related Art In recent years, since the combustion gas temperature of a gas turbine used in a thermal power plant such as a combined power generation system has risen to 1300 to 1500 ° C., many gas turbine materials excellent in heat resistance have been developed. Has been done.
【０００３】また、ガスタービン運転時には、ローター
の回転や、高速で流れる高温ガス、冷却空気の通過等に
伴って、様々な個所で振動が発生する。Further, during operation of the gas turbine, vibrations are generated at various points due to rotation of the rotor, passage of high-temperature gas flowing at high speed, passage of cooling air, and the like.
【０００４】嵌合（はめ込み）により組み上げられた部
材で振動が発生した場合には、部材同士の接触部で摩耗
が発生し、高温下で摩耗損傷が生じる場合がある。摩耗
損傷が生じる個所には、耐摩耗性に優れた材料やコーテ
ィング処理の適用が必要とされる。When vibration is generated in the members assembled by fitting (fitting), wear may occur at the contact portion between the members, resulting in wear damage at high temperature. Where wear damage occurs, it is necessary to apply a material having excellent wear resistance or a coating treatment.
【０００５】これまでに耐摩耗コーティングとして、Ｃ
ｏ合金のステライトを大気プラズマ溶射した例や、Ｃｒ
3Ｃ2等のクロム炭化物相をニッケル−クロム合金のバイ
ンダ材料と混合して、高速フレーム溶射（ＨＶＯＦ：Ｈ
igh Ｖelocity Ｏxｙ-Ｆuel）によりガスタービン材料
に施工した例が報告されている。So far, C has been used as an abrasion resistant coating.
Example of atmospheric plasma spraying of stellite of o alloy, Cr
A chromium carbide phase such as 3 C 2 is mixed with a binder material of a nickel-chromium alloy, and high speed flame spraying (HVOF: H
An example of applying it to a gas turbine material has been reported by igh Velocity Oxy-Fuel).
【０００６】クロム炭化物コーティングを、ガスタービ
ン部材に適用して摩耗損傷を低減した例としては特願平
８−５３４９４号，特願平９−１９１５５４号公報等が
挙げられる。[0006] Japanese Patent Application No. 8-53494 and Japanese Patent Application No. 9-191554 can be cited as examples of applying a chromium carbide coating to a gas turbine member to reduce wear damage.
【０００７】[0007]
【発明が解決しようとする課題】ガスタービン部材で生
じる高温摩耗損傷は、そのメカニズムが複雑で部材の使
用環境により摩耗状態は大きく変化する。そのため部材
に応じて、適用するコーティング材料の種類、および、
接触部材の組合せの適切な選択が必要となる。The mechanism of high temperature wear damage that occurs in a gas turbine member is complicated, and the wear state changes greatly depending on the environment in which the member is used. Therefore, depending on the member, the type of coating material to be applied, and
Proper selection of contact member combinations is required.
【０００８】摩耗条件が厳しいガスタービン部材の一つ
に、燃焼器ライナから高温ガスをタービン入口に導くト
ランジションピース（尾筒）がある。One of the gas turbine members that are subject to severe wear conditions is a transition piece (tail pipe) that guides high temperature gas from the combustor liner to the turbine inlet.
【０００９】トランジションピースは、高温強度を考慮
してＮ２６３等のニッケル基合金で構成され、前部が円
形、後方部が矩形という複雑な形状を有する。そして、
最後部に取付けられた矩形の額縁と呼ばれる部分の周囲
にスリットを設け、該スリット間に金属薄板のシール材
を挟み込んで、トランジションピースと初段静翼とを嵌
合している。また、同様のシール構造で隣接するトラン
ジションピース同士も嵌合している。The transition piece is made of a nickel base alloy such as N263 in consideration of high temperature strength, and has a complicated shape such that the front portion is circular and the rear portion is rectangular. And
A slit is provided around a portion called a rectangular frame which is attached to the rearmost portion, and a sealing material made of a thin metal plate is sandwiched between the slits to fit the transition piece and the first stage stationary blade. Adjacent transition pieces are also fitted to each other with the same seal structure.
【００１０】ガスタービン稼動時において、トランジシ
ョンピースの額縁部は５００℃を超える高温と、１００
Ｈｚ以上の高周波数の振動とに同時に曝されるため、長
時間の運転により額縁とシールの接触部で大きな摩耗損
傷が生じる。特に、トランジションピースと初段静翼と
を嵌合するフローティングシールと呼ばれる部材におい
ては、静翼側から額縁側にシールが押し付けられるよう
な力が作用するため、額縁最後部とフローティングシー
ルの接触部で顕著な摩耗が発生し、問題となる場合が多
い。During operation of the gas turbine, the frame portion of the transition piece is exposed to a high temperature exceeding 500 ° C.
Since it is simultaneously exposed to vibrations of high frequency of Hz or higher, long-time operation causes large abrasion damage at the contact portion between the frame and the seal. In particular, in a member called a floating seal that fits the transition piece and the first stage stationary blade, a force that pushes the seal from the stationary blade side to the frame side acts, so it is remarkable at the contact portion between the frame last part and the floating seal. It often causes serious wear and causes a problem.
【００１１】ここで、トランジションピースの接触部に
クロム炭化物をコーティングしても、摩耗損傷を十分に
防止できない場合がある。これは振動周波数が１００Ｈ
ｚ以上と比較的高い場合には、額縁とシールの両面にコ
ーティングを施して摺動すると、クロム炭化物粒子が相
手側コーティング中の炭化物粒子を削り取り、クロム炭
化物の脱落が生じるためである。Here, even if the contact portion of the transition piece is coated with chromium carbide, it may not be possible to sufficiently prevent wear damage. This has a vibration frequency of 100H
When z is relatively high, coating both surfaces of the frame and the seal and sliding them causes the chromium carbide particles to scrape off the carbide particles in the coating on the other side, causing the chromium carbide to fall off.
【００１２】また、クロム炭化物コーティングをトラン
ジションピース材のニッケル基合金と摺動させると、硬
質なクロム炭化物がニッケル基合金表面を切削するアブ
レッシブ摩耗の状態となり、ニッケル基合金の摩耗損傷
を増大する結果となる。Further, when the chromium carbide coating is slid on the nickel-base alloy of the transition piece material, the hard chromium carbide is in an abrasive wear state for cutting the surface of the nickel-base alloy, resulting in an increase in wear damage of the nickel-base alloy. Becomes
【００１３】このように、クロム炭化物コーティングを
トランジションピース額縁部へ適用しても、相手材の選
択が適切でない場合は、コーティング層あるいは相手材
のいずれかを大きく摩耗してしまう結果となる。As described above, even when the chromium carbide coating is applied to the frame portion of the transition piece, if the mating material is not properly selected, either the coating layer or the mating material will be greatly worn.
【００１４】本発明の目的は、上記に鑑み、燃焼器トラ
ンジションピースの額縁部とフローティングシール嵌合
部で発生する摩耗損傷を防止するための耐摩耗構造を有
するガスタービン燃焼器を提供することにある。In view of the above, an object of the present invention is to provide a gas turbine combustor having a wear-resistant structure for preventing wear damage occurring at a frame portion of a combustor transition piece and a floating seal fitting portion. is there.
【００１５】[0015]
【課題を解決するための手段】本発明者らは、クロム炭
化物コーティングの相手材について検討し、耐摩耗性に
優れた耐熱材料としてコバルト基合金に着目した。ステ
ライトＮｏ.６のような耐摩耗性に優れたコバルト基合
金は通常、組織中に多量の炭化物を含むことから、炭化
物の効果により耐摩耗性が優れると従来は考えられてい
る。[Means for Solving the Problems] The present inventors have investigated a counterpart material of a chromium carbide coating and have focused on a cobalt-based alloy as a heat resistant material having excellent wear resistance. Since cobalt-based alloys such as Stellite No. 6 which have excellent wear resistance usually contain a large amount of carbide in the structure, it is conventionally considered that the wear resistance is excellent due to the effect of the carbide.
【００１６】しかし、このステライトＮｏ.６をクロム
炭化物コーティングの相手材として高温下で摺動させた
場合には、クロム炭化物コーティング側に大きな摩耗損
傷が生じてしまい、好ましい結果が得られなかった。However, when this stellite No. 6 was slid at a high temperature as a counterpart material for the chromium carbide coating, a large amount of abrasion damage was caused on the chromium carbide coating side, and a desirable result was not obtained.
【００１７】一方、炭素含有量が０.１重量％と少なく
炭化物の形成が非常に少ないＨＳ２５のようなコバルト
基合金を、クロム炭化物コーティングの相手材として選
び試験した場合には、両者共に摩耗損傷が小さくなり、
非常に優れた耐摩耗性を示すことを見出した。On the other hand, when a cobalt-based alloy such as HS25, which has a low carbon content of 0.1% by weight and very little carbide formation, is selected as a counterpart material for the chromium carbide coating and tested, both of them show wear damage. Becomes smaller,
It has been found that it exhibits very good wear resistance.
【００１８】炭化物の形成が少ないコバルト基合金（固
溶体型コバルト基合金）は、高温で摩耗を受けると摺動
表面に摩耗紛が堆積して、緻密な付着層を形成する。こ
のコバルト基合金の付着層は密着性が高く、摺動の際の
摩擦抵抗を低下させて、摩耗損傷を減少すると推測され
る。一方、ニッケル基合金が摩耗した際に摺動部表面に
形成される付着層は、密着性が低いため容易に表面から
脱落し、摩耗損傷の低下に繋がらないと考えた。When a cobalt-based alloy (solid solution type cobalt-based alloy) in which carbides are scarcely formed is subjected to wear at high temperatures, wear powder is deposited on the sliding surface to form a dense adhesion layer. It is presumed that the adhesion layer of the cobalt-based alloy has high adhesiveness, reduces frictional resistance during sliding, and reduces wear damage. On the other hand, it was considered that the adhesion layer formed on the surface of the sliding portion when the nickel-based alloy was worn was easily removed from the surface due to its low adhesiveness and did not lead to a reduction in wear damage.
【００１９】また、固溶体型コバルト基合金を、クロム
炭化物コーティングの相手材として高温ですべり摩耗さ
せた場合には、コーティング層の摺動表面に相手材のコ
バルト基合金摩耗紛がより多く付着する傾向がある。こ
れにより、コーティングのクロム炭化物粒子が付着層に
覆われるため、クロム炭化物のコーティングからの脱落
や、クロム炭化物の切削による相手材の損傷が無くな
り、摩耗損傷が著しく低下することを見出した。When a solid solution type cobalt-based alloy is used as a counterpart of a chromium carbide coating and is subjected to sliding wear at high temperatures, a larger amount of the cobalt-based alloy wear powder of the counterpart is likely to adhere to the sliding surface of the coating layer. There is. As a result, it was found that since the chromium carbide particles of the coating are covered with the adhesion layer, the chromium carbide is not dropped from the coating and the damage of the counterpart material due to the cutting of the chromium carbide is eliminated, and the wear damage is significantly reduced.
【００２０】上記に基づき、トランジションピースの高
温摩耗損傷を抑制するのに最も有効な方法は、額縁とフ
ローティングシールの接触部を、固溶体型コバルト基合
金とクロム炭化物コーティングとの組合せとすることで
ある。ＨＳ２５等の固溶体型コバルト基合金は、容易に
薄板状に加工することが可能で、コバルト基合金でシー
ルを作製し額縁側にクロム炭化物コーティングを施工す
ることが最も容易な対策である。Based on the above, the most effective method for suppressing the high temperature wear damage of the transition piece is to use the combination of the solid solution type cobalt base alloy and the chromium carbide coating as the contact portion between the frame and the floating seal. . A solid solution type cobalt-based alloy such as HS25 can be easily processed into a thin plate, and the easiest measure is to make a seal with the cobalt-based alloy and apply a chromium carbide coating on the frame side.
【００２１】しかし、トランジションピースは厳しい摺
動環境下で使用されるため、タービン運転中にクロム炭
化物コーティング層に損傷が生じて、部分的に剥離を起
こす可能性も考えられる。However, since the transition piece is used in a severe sliding environment, there is a possibility that the chromium carbide coating layer may be damaged during operation of the turbine to cause partial peeling.
【００２２】ニッケル基合金表面にクロム炭化物をコー
ティングした場合には、コーティング層に剥離が生じた
場合、ニッケル基合金が直接摩耗を受けるため、摩耗損
傷が加速される懸念がある。従って、この構成の場合
は、長期安定性の点で課題がある。In the case where the surface of the nickel-base alloy is coated with chromium carbide, if the coating layer is peeled off, the nickel-base alloy is directly abraded, so that the wear damage may be accelerated. Therefore, this configuration has a problem in terms of long-term stability.
【００２３】一方、本発明のコバルト基合金上にコーテ
ィングを施した場合は、コーティングが剥離しても基材
のコバルト基合金にある程度の耐摩耗性があるため、摩
耗損傷が加速度的に進行すると云う問題は解消される。On the other hand, when a coating is applied to the cobalt-based alloy of the present invention, even if the coating is peeled off, the cobalt-based alloy of the base material has a certain degree of wear resistance, so that wear damage accelerates. This problem is solved.
【００２４】トランジションピースの摩耗損傷低減に最
も有効な対策として、本発明は、炭素含有量の少ない固
溶体型コバルト基合金でフローティングシールを作製
し、シール材と同材質の薄板材をトランジションピース
額縁側摺動面に溶接により取付けて、フローティングシ
ールと額縁貼板表面のいずれか一方にのみ、クロム炭化
物を主体とした耐摩耗コーティングを施すことにある。As the most effective measure for reducing the wear damage of the transition piece, the present invention produces a floating seal from a solid solution type cobalt-based alloy having a low carbon content, and uses a thin plate material of the same material as the sealing material on the transition piece frame side. It is attached to the sliding surface by welding, and a wear-resistant coating mainly composed of chromium carbide is applied to only one of the floating seal and the frame sticking plate surface.
【００２５】[0025]
【発明の実施の形態】本発明のクロム炭化物コーティン
グにおいて、硬質相の炭化物には高温安定性に優れたＣ
ｒ3Ｃ2粒子を使用することが好ましい。また、Ｃｒ3Ｃ2
粒子のみを溶射原料とすると、皮膜の脆化や密着性低下
が生じるため、粒子のバインダとして延性なニッケル−
クロム合金粉末と混合して成膜することが好ましい。BEST MODE FOR CARRYING OUT THE INVENTION In the chromium carbide coating of the present invention, C which is excellent in high temperature stability is used for the hard phase carbide.
It is preferred to use r 3 C 2 particles. Also, Cr 3 C 2
If only the particles are used as the thermal spraying material, the coating becomes brittle and the adhesiveness deteriorates.
It is preferable to form a film by mixing with a chromium alloy powder.
【００２６】皮膜中のＣｒ3Ｃ2粒子の含有量が高いほど
高温耐摩耗特性は向上するが、Ｃｒ 3Ｃ2粒子の含有量が
９５％を超えると皮膜の延性が低下し好ましくない。一
方、Ｃｒ3Ｃ2粒子含有量が６５％未満の場合は、耐摩耗
特性が不足するため好ましくない。Cr in the film3C2The higher the particle content
High temperature wear resistance is improved, but Cr 3C2The content of particles
If it exceeds 95%, the ductility of the coating is lowered, which is not preferable. one
One, Cr3C2Wear resistance when the particle content is less than 65%
It is not preferable because the characteristics are insufficient.
【００２７】バインダのニッケル−クロム合金において
は、クロム含有量が１５％未満では高温耐酸化特性が不
足し、３５％を超えると延性が低下する。従ってバイン
ダ合金中のクロム含有量は１５〜３５％とすることが好
ましい。In the nickel-chromium alloy as the binder, if the chromium content is less than 15%, the high temperature oxidation resistance is insufficient, and if it exceeds 35%, the ductility is deteriorated. Therefore, the chromium content in the binder alloy is preferably 15-35%.
【００２８】成膜プロセスとしては、緻密で密着性の高
い皮膜を形成できるＨＶＯＦを用いることが好ましい。
大気中または減圧雰囲気中でプラズマ溶射により成膜を
行うと、原料粉末が高温に加熱されるため、Ｃｒ3Ｃ2粒
子が分解し、構造変化や皮膜の軟化が生じて、耐摩耗性
が低下する可能性があるので好ましくない。As the film forming process, it is preferable to use HVOF capable of forming a dense and highly adherent film.
When a film is formed by plasma spraying in the air or in a reduced pressure atmosphere, the raw material powder is heated to a high temperature, so the Cr 3 C 2 particles are decomposed, the structure changes and the film softens, and wear resistance decreases. This is not preferable because it may occur.
【００２９】コーティング層の厚さについては、厚さが
０.１ｍｍ未満の場合は長時間使用中に皮膜が摩滅し、
耐摩耗性が不足するため好ましくない。また、厚さが
０.６ｍｍを超えると皮膜の剥離が生じ易くなるため好
ましくない。従って、コーティング層の厚さは０.１〜
０.６ｍｍとすることが好ましい。Regarding the thickness of the coating layer, when the thickness is less than 0.1 mm, the coating wears out during long-term use,
It is not preferable because the abrasion resistance is insufficient. Further, if the thickness exceeds 0.6 mm, peeling of the film is likely to occur, which is not preferable. Therefore, the thickness of the coating layer is 0.1-
It is preferably 0.6 mm.
【００３０】〔実施例 １〕図１は、各種耐熱合金を組
合せた場合の高温すべり摩耗試験による摩耗損傷量を示
すグラフである。試験温度は７００℃とし、振動条件は
振幅１.０ｍｍ、周波数は１００Ｈｚとした。また、摩
耗試験片は全長４０ｍｍの蒲鉾型とし、形状が同じ１対
の試験片の曲面部分を交差して接触させ、５ｋｇの荷重
を加えて摺動させた。Example 1 FIG. 1 is a graph showing the amount of wear damage by a high temperature sliding wear test when various heat resistant alloys were combined. The test temperature was 700 ° C., the vibration condition was an amplitude of 1.0 mm, and the frequency was 100 Hz. Further, the wear test piece was a kamaboko type having a total length of 40 mm, and the curved surface portions of a pair of test pieces having the same shape were crossed and brought into contact with each other, and a load of 5 kg was applied for sliding.
【００３１】摩耗量の数値は、試験片表面の摩耗部にお
いて、表面粗さ計により凹凸のプロファイルを測定し、
プロファイル中の最大摩耗深さを記録した場合の値であ
る。なお、摩耗面に相手材の摩耗粒子が付着して盛上り
が生じた際の最大盛上り高さを、摩耗量の負の値で示し
た。The numerical value of the amount of wear is determined by measuring the profile of the unevenness on the worn part of the surface of the test piece with a surface roughness meter.
It is a value when the maximum wear depth in the profile is recorded. The maximum rise height when wear particles of the mating material adhered to the wear surface and caused rise was shown by a negative value of the wear amount.
【００３２】合金試験材として、トランジションピース
材のニッケル基合金Ｎ２６３，固溶体型コバルト基合金
のＨＳ２５および析出強化型コバルト基合金のＦＳＸ４
１４を使用した。またコーティング材としては、ＨＳ２
５の表面にＨＶＯＦによりクロム炭化物を成膜した材料
（ＣｒＣコート）と、大気溶射によりステライトＮｏ.
６を成膜した材料を使用した。試験に使用した合金およ
びステライトＮｏ.６の化学組成を表１に示す。As alloy test materials, nickel-based alloy N263 as transition piece material, HS25 as solid solution type cobalt-based alloy and FSX4 as precipitation strengthened cobalt-based alloy.
14 was used. As a coating material, HS2
Material (CrC coating) with a chromium carbide film formed by HVOF on the surface of No. 5 and Stellite No. 5 by atmospheric spraying.
The material for which 6 was deposited was used. Table 1 shows the chemical compositions of the alloy and Stellite No. 6 used in the test.
【００３３】[0033]
【表１】
ＨＳ２５は、炭素の添加量が０.１％と少ないために組
織中の炭化物量が少なく、加工性に優れている。一方、
ＨＳ２５の比較材として用いたＦＳＸ４１４は、炭素量
が０.２５％と多いため組織中に多量のクロム炭化物や
タングステン炭化物が析出して材料が強化されている。
そのためＨＳ２５に較べて高温強度に優れているが、延
性は低下する。[Table 1] Since HS25 has a small amount of carbon added of 0.1%, it has a small amount of carbide in the structure and is excellent in workability. on the other hand,
Since FSX414 used as a comparative material for HS25 has a large carbon content of 0.25%, a large amount of chromium carbide or tungsten carbide is precipitated in the structure to strengthen the material.
Therefore, it is superior in high-temperature strength to HS25, but ductility is reduced.
【００３４】また、ステライトＮｏ.６は耐摩耗性を高
めるために炭素の添加量を１％以上に増加している。ク
ロム炭化物コーティングにおいては、Ｃｒ3Ｃ2粒子とバ
インダのニッケル−クロム合金の混合粉末を原料とし
た。その際、Ｃｒ3Ｃ2粒子の含有量は体積比で８０％と
した。In addition, in Stellite No. 6, the amount of carbon added is increased to 1% or more in order to improve wear resistance. In the chromium carbide coating, a mixed powder of Cr 3 C 2 particles and a nickel-chromium alloy binder was used as a raw material. At that time, the content of Cr 3 C 2 particles was set to 80% by volume.
【００３５】図１の上段部に示した３つの比較材として
は、それぞれＮ２６３同士、ＨＳ２５とＮ２６３、ＨＳ
２５同士の合金素材間による摩耗試験結果である。The three comparative materials shown in the upper part of FIG. 1 include N263, HS25 and N263, HS, respectively.
It is a wear test result between 25 alloy materials.
【００３６】Ｎ２６３の場合は、同種材の組合せとＨＳ
２５とを組合せた場合の両方で、摩耗量は３００〜４０
０μｍ以上の大きな値を示している。In the case of N263, a combination of similar materials and HS
The wear amount is 300 to 40 in both cases of combination with 25.
A large value of 0 μm or more is shown.
【００３７】一方、ＨＳ２５の場合は、Ｎ２６３との組
合せ、同種材の組合せの両方の試験結果共に、上記のＮ
２６３の場合に較べて摩耗量が低下しており、摩耗損傷
の低減効果があることが分かる。On the other hand, in the case of HS25, both the test results of the combination with N263 and the combination of the same kind of material are both
The wear amount is lower than that of the case of No. 263, and it can be seen that there is an effect of reducing wear damage.
【００３８】しかしながら、ＨＳ２５同種材の組合せに
おいても、試験材の片方が２００μｍ以上摩耗してお
り、合金素材同士の接触では摩耗損傷の防止に十分な効
果が得られないことが明らかになった。However, even in the combination of the HS25 homogenous materials, one of the test materials was abraded by 200 μm or more, and it was revealed that the contact between the alloy materials was not sufficient to prevent abrasion damage.
【００３９】図１の４段目以下にはＣｒＣコート材を用
いた試験結果を示す。比較材のＣｒＣコートとＮ２６３
の組合せにおいては、ＣｒＣコート側は摩耗減量が数μ
ｍ程度であり、殆ど減肉が生じておらず、耐摩耗保護層
として優れていることが分かる。しかし、相手材のＮ２
６３の摩耗量は４００μｍ以上と非常に大きく、金属素
材の組合せよりも損傷が増大している。The test results using the CrC coating material are shown below the fourth row in FIG. CrC coating of comparison material and N263
In the combination, the wear loss on the CrC coated side is several μ
It is about m, and it is understood that there is almost no wall thinning and it is excellent as a wear-resistant protective layer. However, the other material N2
The wear amount of 63 is 400 μm or more, which is very large, and the damage is larger than that of the combination of metal materials.
【００４０】一方、５段目に示す本発明のＣｒＣコート
材とＨＳ２５を組合せた場合には、ＣｒＣコート材には
減肉が起こらず、相手材の粒子が付着した盛上りが生じ
るだけであった。相手材のＨＳ２５摩耗量も約１００μ
ｍとなり、金属素材の中では最小の値を示した。ＣｒＣ
コート材には３０μｍ以上の盛上りが見られるが、これ
はＨＳ２５の摩耗紛が摩耗面から排出されずに付着した
ためである。On the other hand, when the CrC coating material of the present invention shown in the fifth row and HS25 are combined, the CrC coating material does not undergo wall thinning, but only the swelling of the particles of the mating material occurs. It was HS25 wear amount of mating material is also about 100μ
m, which is the smallest value among metal materials. CrC
A rise of 30 μm or more is observed in the coating material, but this is because the abrasion powder of HS25 adheres without being discharged from the abrasion surface.
【００４１】相手材がＮ２６３の場合にも盛上りが見ら
れるが、ＨＳ２５の方の盛上り高さが約２倍になり、摩
耗紛の凝着が促進されることが分かった。Although swelling was also observed when the mating material was N263, it was found that the swelling height of the HS25 was approximately doubled and the adhesion of wear powder was promoted.
【００４２】このＣｒＣコート表面の安定な付着層の形
成により、摺動面の摩擦抵抗が低下してＨＳ２５の摩耗
量が低下したものと推定される。It is presumed that the formation of the stable adhesion layer on the surface of the CrC coat reduced the frictional resistance of the sliding surface and reduced the wear amount of the HS25.
【００４３】一方、下段に示す比較材のＣｒＣコート材
とＦＳＸ４１４の組合せでは、ＣｒＣコート側に４００
μｍ程度の大きな摩耗減量が生じている。これはＦＳＸ
４１４が炭化物で強化されているために、この炭化物に
よりＣｒＣコート側の炭化物が切削されて脱落したため
と推定される。On the other hand, in the combination of the comparative material CrC coating material and FSX414 shown in the lower part, the CrC coating side has 400
A large wear loss of about μm occurs. This is FSX
It is presumed that the carbide on the CrC coat side was cut and dropped due to the carbide because 414 was reinforced with the carbide.
【００４４】また、比較材のＣｒＣコート材とステライ
トコート材の組合せにおいても、ＦＳＸ４１４の場合と
同様に、ＣｒＣコート側に３００μｍ以上の大きな摩耗
減量が認められた。これもステライトが多量の炭化物を
含むことで生じたと考えられる。Also in the combination of the CrC coating material and the stellite coating material of the comparative material, as in the case of FSX414, a large abrasion loss of 300 μm or more was recognized on the CrC coating side. It is considered that this also occurred because the stellite contained a large amount of carbide.
【００４５】最下段のＣｒＣコート材同士の比較材同士
の組合せでは、それぞれの試験材が１８０μｍ程度の損
傷を受けている。これも互いのクロム炭化物粒子が相手
側コーティング中の炭化物粒子を削り取り、クロム炭化
物の脱落が生じたためと推定される。In the combination of the CrC coated materials in the lowermost stage and the comparative materials, each test material was damaged by about 180 μm. It is presumed that this is also because the chromium carbide particles of each other scraped off the carbide particles in the coating on the other side, and the chromium carbide fell off.
【００４６】このように、耐熱合金にクロム炭化物コー
ティングを施した場合の高温すべり摩耗現象は、相手材
の組合せにより挙動が大きく変化する。相手材が延性な
金属の場合は、クロム炭化物コーティングには殆ど摩耗
による減肉が起こらず、コーティングの保護効果が非常
に有効に作用する。しかし、その反面、相手金属にある
程度の耐摩耗特性が備わっていないと、相手材の摩耗損
傷を低減することはできない。As described above, the behavior of the high temperature sliding wear phenomenon in the case where the heat resistant alloy is coated with the chromium carbide changes greatly depending on the combination of the mating materials. When the mating material is a ductile metal, the chromium carbide coating hardly loses its thickness due to wear, and the protective effect of the coating acts very effectively. However, on the other hand, if the mating metal does not have a certain degree of wear resistance, it is impossible to reduce the wear damage of the mating material.
【００４７】また、クロム炭化物コーティング同士や、
硬質粒子を含む金属を相手材とした場合には、相手側の
硬質粒子により炭化物が切削されて、コーティングが損
傷してしまう。摩耗損傷の低減に最も有効なのは、接触
面をクロム炭化物コーティングと、ＨＳ２５のような固
溶体型コバルト基合金の組合せとすることである。Also, chromium carbide coatings,
When a metal containing hard particles is used as the mating material, the hard particles on the mating side cut the carbide and damage the coating. The most effective way to reduce wear damage is to combine the contact surface with a chromium carbide coating and a solid solution cobalt-based alloy such as HS25.
【００４８】〔実施例 ２〕本発明で提示した、クロム
炭化物コーティングと固溶体型コバルト基合金の耐摩耗
性に優れた材料の組合せを、実機ガスタービンのトラン
ジションピースに適用した例を説明する。Example 2 An example in which the combination of the chromium carbide coating and the solid solution type cobalt-based alloy material having excellent wear resistance presented in the present invention is applied to a transition piece of an actual gas turbine will be described.
【００４９】図２は、本実施例で用いたトランジション
ピースの概略を示す斜視図である。トランジションピー
ス本体１の後方の額縁２の上下に取付けられ、静翼と額
縁を嵌合するシールがフローティングシール３，３’で
ある。また、額縁２の側面に取付けられ額縁同士を嵌合
するシールをサイドシール４，４’と呼ぶ。FIG. 2 is a perspective view showing the outline of the transition piece used in this embodiment. Floating seals 3 and 3 ′ are seals that are attached above and below the frame 2 behind the transition piece body 1 and that fit the stationary blade and the frame together. Further, the seals attached to the side surfaces of the frame 2 and fitting the frames together are referred to as side seals 4 and 4 '.
【００５０】図３は、額縁２へのフローティングシール
の取付け状態を示す斜視図である。フローティングシー
ル３，３’は、湾曲した断面形状を有する薄板材であ
り、上下２本の各シールは、額縁２の外周部のシール溝
５に図３（ａ）に示す状態で取付けられる。シール取付
け後の状態を図３（ｂ）に示した。上下のフローティン
グシール３，３’の後方に張出した部分は初段静翼と嵌
合する。FIG. 3 is a perspective view showing how the floating seal is attached to the frame 2. The floating seals 3 and 3'are thin plate materials having a curved cross-sectional shape, and the two upper and lower seals are attached to the seal groove 5 on the outer peripheral portion of the frame 2 in the state shown in FIG. 3 (a). The state after the seal is attached is shown in FIG. The portions of the upper and lower floating seals 3 and 3'overhanging rearward fit with the first stage stationary blade.
【００５１】本実施例においては、まず、ＨＳ２５の素
材を加工してフローティングシールを作製し、シールの
摩耗損傷が生じる部分に、ＨＶＯＦによりクロム炭化物
コーティングを施工した。In this example, first, the material of HS25 was processed to prepare a floating seal, and a chromium carbide coating was applied by HVOF to the portion where the seal was worn and damaged.
【００５２】次に、額縁２とシールとの接触部にはＨＳ
２５の保護板６を溶接により取付け、上記部材を組合せ
てトランジションピースを作製した。Next, HS is attached to the contact portion between the frame 2 and the seal.
Twenty-five protective plates 6 were attached by welding and the above members were combined to produce a transition piece.
【００５３】図４は、本発明の摩耗対策を施したフロー
ティングシールと額縁を実機ガスタービンに取付けた際
の構造を示す模式断面図である。図４は、図３（ｂ）の
断面Ａにおける上部フローティングシール取付け部の模
式断面図である。FIG. 4 is a schematic cross-sectional view showing the structure when the floating seal and the frame according to the present invention, which are provided with measures against wear, are attached to an actual gas turbine. FIG. 4 is a schematic cross-sectional view of the upper floating seal attachment portion in the cross section A of FIG.
【００５４】フローティングシール３と額縁２との間で
は、シールが静翼側から額縁側に押し付けられるような
力が作用し、額縁の最後部とフローティングシール内面
の静翼側の接触部で顕著な摩耗が発生する。そのため、
図４で示すようにフローティングシール３および額縁２
の部位に対して、コーティング施工と保護板６の取付け
を行った。A force is exerted between the floating seal 3 and the frame 2 such that the seal is pressed from the stationary blade side to the frame side, and significant wear is caused at the contact portion between the last portion of the frame and the inner surface of the floating seal on the stationary blade side. Occur. for that reason,
As shown in FIG. 4, the floating seal 3 and the frame 2
The coating was applied and the protective plate 6 was attached to the part.
【００５５】一方、額縁のシール溝５や静翼シール溝８
とフローティングシール３間の接触部においては、摩耗
損傷は比較的小さいことから、コーティングや保護板取
付けの摩耗対策は行なっていない。なお、下部のフロー
ティングシールにおいても、コーティングと保護板の取
付け位置は同じとした。On the other hand, the frame seal groove 5 and the stationary blade seal groove 8
Since the wear damage is relatively small in the contact portion between the floating seal 3 and the floating seal 3, no countermeasures against wear such as coating and attachment of the protective plate are taken. In the lower floating seal, the coating and the protective plate were installed at the same position.
【００５６】上記したフローティングシールへのクロム
炭化物コーティング、および、額縁２への保護板６の取
付けの摩耗対策を施したトランジションピースを、実機
ガスタービンに取付けて運転試験を行なった。その結
果、摩耗防止対策を行なわない場合に比べてフローティ
ングシール，額縁材共に摩耗損傷が大きく改善されるこ
とを確認した。An operation test was carried out by mounting the transition piece having the above-mentioned chrome-carbide coating on the floating seal and the wear prevention measures for mounting the protective plate 6 on the frame 2 on the actual gas turbine. As a result, it was confirmed that the wear damage of both the floating seal and the frame material was greatly reduced compared to the case where no wear prevention measures were taken.
【００５７】〔実施例 ３〕本実施例では、額縁２に取
付けたＨＳ２５製の保護板６の表面に、ＨＶＯＦにより
クロム炭化物コーティングを施工する一方で、フローテ
ィングシール側にはコーティングを施工しない状態でト
ランジションピースを構成し、実機ガスタービンに適用
した。[Embodiment 3] In this embodiment, the surface of the HS25 protective plate 6 attached to the frame 2 is coated with chromium carbide by HVOF, while the floating seal is not coated. A transition piece was constructed and applied to an actual gas turbine.
【００５８】図５は、フローティングシール（上部）の
取付け構造の模式断面図を示す。額縁２の保護板６の取
付け位置は実施例２と同様とし、溶接により保護板６を
取付けた後にコーティングを施工した。FIG. 5 is a schematic sectional view of a floating seal (upper) mounting structure. The mounting position of the protective plate 6 on the frame 2 was the same as in Example 2, and coating was applied after the protective plate 6 was mounted by welding.
【００５９】本実施例のコーティングは、実施例２と逆
の額縁側に施工しているが、フローティングシールと額
縁の接触部における材料組合せは、クロム炭化物コーテ
ィングとＨＳ２５である。これらも実機ガスタービンに
よる運転試験により、実施例２と同様に摩耗防止対策を
行なわない場合に比べて、摩耗損傷の防止に有効なこと
を確認した。The coating of this example is applied to the frame side opposite to that of Example 2, but the material combination at the contact portion between the floating seal and the frame is chromium carbide coating and HS25. As a result of an operation test using an actual gas turbine, it was confirmed that these were more effective in preventing wear damage than in the case where no wear prevention measures were taken as in Example 2.
【００６０】[0060]
【発明の効果】本発明のクロム炭化物コーティングと固
溶体型コバルト基合金保護板の組合せによる高温耐摩耗
構造を、ガスタービンのトランジションピースに適用す
ることにより、摩耗損傷を大幅に低減することが可能と
なる。その結果、トランジションピース額縁材およびシ
ール材の使用寿命の延長による交換頻度の低減や、ガス
タービンの信頼性向上が可能となる。EFFECTS OF THE INVENTION By applying the high temperature wear resistant structure of the present invention, which is a combination of the chromium carbide coating and the solid solution type cobalt-based alloy protective plate, to a transition piece of a gas turbine, it is possible to significantly reduce wear damage. Become. As a result, it is possible to reduce the replacement frequency by extending the service life of the transition piece frame material and the sealing material and improve the reliability of the gas turbine.
【図１】各種耐熱合金を組合せた場合の高温すべり摩耗
試験による摩耗損傷量を示すグラフである。FIG. 1 is a graph showing the amount of wear damage by a high temperature sliding wear test when various heat resistant alloys are combined.
【図２】実施例２で用いたトランジションピースの概略
を示す斜視図である。FIG. 2 is a perspective view showing an outline of a transition piece used in Example 2.
【図３】実施例２で用いたトランジションピースへのフ
ローティングシールの取付け状態を示す斜視図である。FIG. 3 is a perspective view showing how a floating seal is attached to a transition piece used in Example 2.
【図４】実施例２の摩耗対策を施したフローティングシ
ールと額縁とを実機ガスタービンに取付けた模式断面図
である。FIG. 4 is a schematic cross-sectional view in which a floating seal and a frame according to the second embodiment, which are provided with measures against wear, are attached to an actual gas turbine.
【図５】実施例３の摩耗対策を施したフローティングシ
ールと額縁とを実機ガスタービンに取付けた模式断面図
である。FIG. 5 is a schematic cross-sectional view in which a floating seal and a frame, which are provided with measures against wear of Example 3, are attached to an actual gas turbine.
１…トランジションピース本体、２…額縁、３，３’…
フローティングシール、４，４’…サイドシール、５…
シール溝、６…保護板、７…静翼、８…静翼シール溝。1 ... Transition piece body, 2 ... Frame, 3, 3 '...
Floating seal, 4, 4 '... Side seal, 5 ...
Seal groove, 6 ... Protective plate, 7 ... Stator blade, 8 ... Stator blade seal groove.
フロントページの続き (72)発明者 市川 国弘 茨城県日立市幸町三丁目１番１号 株式会 社日立製作所火力・水力事業部内 (72)発明者 新谷 静馬 広島県東広島市鏡山三丁目９番１号 中国 電力株式会社内 (72)発明者 西田 秀高 広島県東広島市鏡山三丁目９番１号 中国 電力株式会社内 (72)発明者 三好 康光 広島県東広島市鏡山三丁目９番１号 中国 電力株式会社内 Ｆターム(参考） 4K031 AA08 AB02 CB14 CB22 CB45 DA01 Continued front page (72) Inventor Kunihiro Ichikawa 3-1-1 Sachimachi, Hitachi City, Ibaraki Prefecture Stock Association Hitachi, Ltd., Thermal Power & Hydro Power Division (72) Inventor Shizuma Shintani 3-9-1, Kagamiyama, Higashihiroshima City, Hiroshima, China Electric power company (72) Inventor Hidetaka Nishida 3-9-1, Kagamiyama, Higashihiroshima City, Hiroshima, China Electric power company (72) Inventor Yasumitsu Miyoshi 3-9-1, Kagamiyama, Higashihiroshima City, Hiroshima, China Electric power company F term (reference) 4K031 AA08 AB02 CB14 CB22 CB45 DA01
Claims (3)
ョンピース（尾筒）と初段静翼とをシール材を介して嵌
合したガスタービン燃焼器において、 化学組成中にクロムを１５〜３０重量％、炭素を０.０
５〜０.２重量％含有するコバルト基合金を基材とし、
表面にクロム炭化物を主成分とする厚さが０.１〜０.６
ｍｍの耐摩耗コーティング処理した板材をシール材と
し、トランジションピース嵌合部におけるシール材のコ
ーティング層との接触部に、シール材と同種のコバルト
基合金板材を取付けたことを特徴とするガスタービン燃
焼器。1. A gas turbine combustor in which a combustor transition piece (tail tube) of a gas turbine for power generation and a first stage stationary blade are fitted with a sealing material, and chromium is contained in the chemical composition in an amount of 15 to 30 wt%. Carbon to 0.0
Based on a cobalt-based alloy containing 5 to 0.2 wt%,
The surface is mainly composed of chromium carbide and has a thickness of 0.1 to 0.6
mm combustion-resistant plate material is used as a seal material, and a cobalt-based alloy plate material of the same type as the seal material is attached to the contact part of the transition piece fitting part with the coating layer of the seal material. vessel.
ョンピース（尾筒）と初段静翼とをシール材を介して嵌
合したガスタービン燃焼器において、 化学組成中にクロムを１５〜３０重量％、炭素を０.０
５〜０.２重量％含有するコバルト基合金をシール材と
し、トランジションピース嵌合部におけるシールとの接
触部に、シール材と同種類のコバルト基合金板材を取付
けた後、該板材表面およびその周囲のシール材と接触す
る領域表面にクロム炭化物を主成分とする厚さが０.１
〜０.６ｍｍの耐摩耗コーティング層を施したことを特
徴とするガスタービン燃焼器。2. A gas turbine combustor in which a combustor transition piece (tail tube) of a gas turbine for power generation and a first-stage stationary blade are fitted with a sealing material, and 15 to 30% by weight of chromium is contained in the chemical composition, Carbon to 0.0
A cobalt-based alloy containing 5 to 0.2% by weight is used as a sealing material, and a cobalt-based alloy plate material of the same type as the sealing material is attached to a contact portion of the transition piece fitting portion with the seal. The thickness of the main component of chromium carbide is 0.1 on the surface of the area that contacts the surrounding sealing material.
A gas turbine combustor characterized by having a wear-resistant coating layer of up to 0.6 mm.
物と混合するバインダ相をニッケル−クロム合金とし、
コーティング層のクロム炭化物含有量が体積比で６５〜
９５％である請求項１または２に記載のガスタービン燃
焼器。3. A nickel-chromium alloy is used as a binder phase mixed with the chromium carbide of the wear-resistant coating layer,
The chromium carbide content of the coating layer is 65-by volume.
Gas turbine combustor according to claim 1 or 2, which is 95%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2001391062A JP3851161B2 (en) | 2001-12-25 | 2001-12-25 | Gas turbine combustor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2001391062A JP3851161B2 (en) | 2001-12-25 | 2001-12-25 | Gas turbine combustor |
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|---|---|
| JP2003185140A true JP2003185140A (en) | 2003-07-03 |
| JP3851161B2 JP3851161B2 (en) | 2006-11-29 |
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|---|---|---|---|
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005337122A (en) * | 2004-05-27 | 2005-12-08 | Ishikawajima Harima Heavy Ind Co Ltd | Gas seal device |
| JP2006214671A (en) * | 2005-02-04 | 2006-08-17 | Hitachi Ltd | Gas turbine combustor |
| US7784264B2 (en) * | 2006-08-03 | 2010-08-31 | Siemens Energy, Inc. | Slidable spring-loaded transition-to-turbine seal apparatus and heat-shielding system, comprising the seal, at transition/turbine junction of a gas turbine engine |
| US7908866B2 (en) | 2005-04-01 | 2011-03-22 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
| JP2014009938A (en) * | 2012-06-27 | 2014-01-20 | General Electric Co <Ge> | Transition duct for gas turbine |
| DE102013205031A1 (en) * | 2013-03-21 | 2014-09-25 | Siemens Aktiengesellschaft | Sealing element for sealing a gap |
| US9677427B2 (en) | 2014-07-04 | 2017-06-13 | Pratt & Whitney Canada Corp. | Axial retaining ring for turbine vanes |
| JP2019112723A (en) * | 2019-03-13 | 2019-07-11 | ヌオーヴォ ピニォーネ ソチエタ レスポンサビリタ リミタータＮｕｏｖｏ Ｐｉｇｎｏｎｅ Ｓ．Ｒ．Ｌ． | Method for treating component to prevent erosion of the component |
| US11391168B2 (en) | 2018-02-28 | 2022-07-19 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor and transition piece assembly |
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| JPH09241818A (en) * | 1996-03-11 | 1997-09-16 | Toshiba Corp | Wear resistant coating for turbine member |
| JPH1137464A (en) * | 1997-07-16 | 1999-02-12 | Toshiba Corp | Liner for gas turbine combustor |
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Patent Citations (6)
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|---|---|---|---|---|
| JPH09241818A (en) * | 1996-03-11 | 1997-09-16 | Toshiba Corp | Wear resistant coating for turbine member |
| JPH1137464A (en) * | 1997-07-16 | 1999-02-12 | Toshiba Corp | Liner for gas turbine combustor |
| JPH11200894A (en) * | 1998-01-12 | 1999-07-27 | Hitachi Ltd | Gas turbine and its compressed air leakage preventing device |
| JP2000225475A (en) * | 1998-11-02 | 2000-08-15 | General Electric Co <Ge> | Method to apply wear resistant material to turbine blade and turbine blade having wear resistant material |
| JP2001317739A (en) * | 2000-05-05 | 2001-11-16 | General Electric Co <Ge> | Combustor having ceramic matrix composite liner |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005337122A (en) * | 2004-05-27 | 2005-12-08 | Ishikawajima Harima Heavy Ind Co Ltd | Gas seal device |
| JP2006214671A (en) * | 2005-02-04 | 2006-08-17 | Hitachi Ltd | Gas turbine combustor |
| JP4668636B2 (en) * | 2005-02-04 | 2011-04-13 | 株式会社日立製作所 | Gas turbine combustor |
| US7908866B2 (en) | 2005-04-01 | 2011-03-22 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
| US7784264B2 (en) * | 2006-08-03 | 2010-08-31 | Siemens Energy, Inc. | Slidable spring-loaded transition-to-turbine seal apparatus and heat-shielding system, comprising the seal, at transition/turbine junction of a gas turbine engine |
| JP2014009938A (en) * | 2012-06-27 | 2014-01-20 | General Electric Co <Ge> | Transition duct for gas turbine |
| DE102013205031A1 (en) * | 2013-03-21 | 2014-09-25 | Siemens Aktiengesellschaft | Sealing element for sealing a gap |
| US9677427B2 (en) | 2014-07-04 | 2017-06-13 | Pratt & Whitney Canada Corp. | Axial retaining ring for turbine vanes |
| US11391168B2 (en) | 2018-02-28 | 2022-07-19 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor and transition piece assembly |
| JP2019112723A (en) * | 2019-03-13 | 2019-07-11 | ヌオーヴォ ピニォーネ ソチエタ レスポンサビリタ リミタータＮｕｏｖｏ Ｐｉｇｎｏｎｅ Ｓ．Ｒ．Ｌ． | Method for treating component to prevent erosion of the component |
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|---|---|
| JP3851161B2 (en) | 2006-11-29 |
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