JP2012503743A - Turbocharger and retaining disk for turbocharger - Google Patents

Turbocharger and retaining disk for turbocharger Download PDF

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JP2012503743A
JP2012503743A JP2011529137A JP2011529137A JP2012503743A JP 2012503743 A JP2012503743 A JP 2012503743A JP 2011529137 A JP2011529137 A JP 2011529137A JP 2011529137 A JP2011529137 A JP 2011529137A JP 2012503743 A JP2012503743 A JP 2012503743A
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turbocharger
holding disk
exhaust gas
resistance
holding
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JP5864256B2 (en
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ジェラルド・シャール
メラニー・ガーベル
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ボーグワーナー インコーポレーテッド
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    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/22—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Abstract

本発明は、特にディーゼルエンジン用のターボ過給機で使用するための保持ディスクであって、樹枝状炭化物析出物を含むオーステナイトベースの構造を有する鉄ベースの合金からなる保持ディスクに関する。  The present invention relates to a holding disk for use in a turbocharger, in particular for diesel engines, comprising an iron-based alloy having an austenite-based structure containing dendritic carbide precipitates.

Description

本発明は、請求項１の前段に記載の、特にディーゼルエンジン用のターボ過給機で使用するための保持ディスク、および請求項４の前段に記載の保持ディスクを備える排気ガスターボ過給機に関する。   The present invention relates to a holding disk for use in a turbocharger, particularly for a diesel engine, as described in the first stage of claim 1, and to an exhaust gas turbocharger comprising the holding disk as described in the first stage of claim 4.

排気ガスターボ過給機は、ピストンエンジンの動力を増加させるためのシステムである。排気ガスターボ過給機では、動力を増加させるために排気ガスのエネルギーが使用される。作業ストロークあたりの混合物のスループットが増加することにより動力が増加する。   An exhaust gas turbocharger is a system for increasing the power of a piston engine. In the exhaust gas turbocharger, the energy of the exhaust gas is used to increase the power. Power is increased by increasing the throughput of the mixture per working stroke.

ターボ過給機は、シャフトおよびコンプレッサを有する排気ガスタービンを実質的に備え、エンジンの吸入口に配置されたコンプレッサがシャフトに接続され、排気ガスタービンおよびコンプレッサのケーシング内に配置されたブレードホイールが回転する。可変のタービン幾何形状を有するターボ過給機の場合、さらに、ブレード軸受リング内に調節ブレードが回転可能に取り付けられ、ターボ過給機のタービンケーシング内に配置された調節リングによって移動される。タービンケーシング内に配置されたリング（前記リングは、保持ディスクとも呼ばれる）は、ブレード軸受リングと共に、調節ブレードによって形成される流れ空間を軸方向で画定する。このリングをブレード軸受リングに所定の距離で締結するために通常はねじが使用され、この距離は、所望の寸法を有する流路を形成するようにスペーサによって所定の高さに設定される。   The turbocharger substantially comprises an exhaust gas turbine having a shaft and a compressor, a compressor disposed at the engine inlet is connected to the shaft, and a blade wheel disposed within the casing of the exhaust gas turbine and the compressor. Rotate. In the case of a turbocharger having a variable turbine geometry, an adjustment blade is also rotatably mounted in the blade bearing ring and is moved by an adjustment ring arranged in the turbocharger turbine casing. A ring arranged in the turbine casing (the ring, also referred to as retaining disk), together with the blade bearing ring, axially defines the flow space formed by the adjusting blade. A screw is usually used to fasten the ring to the blade bearing ring at a predetermined distance, and this distance is set to a predetermined height by a spacer so as to form a flow path having a desired dimension.

保持ディスクの材料には、非常に高い要件が課される。保持ディスクを形成する材料は耐熱性がなければならず、すなわち、最大約９００℃の非常に高い温度でさえ依然として十分な強度を示さなければならない。さらに、材料に対する腐食および摩耗が低減され、したがって極端な動作条件下でも材料の耐性が保証されるように、材料は高い耐摩耗性および対応する耐酸化性を有さなければならない。   Very high requirements are imposed on the material of the holding disk. The material forming the retaining disk must be heat resistant, i.e. it must still exhibit sufficient strength even at very high temperatures up to about 900 ° C. Furthermore, the material must have a high wear resistance and a corresponding oxidation resistance so that the corrosion and wear on the material is reduced and thus the resistance of the material is guaranteed even under extreme operating conditions.

排気ガスターボ過給機およびそれらの個々の構成要素のための耐熱性材料は、欧州特許出願公開第１３９６６２０号から知られている。この文献では、適切な材料は、ある特定の組成を有する材料と考えられ、構成要素の表面が炭化クロム層で被覆されることがあり、材料が少量の小さな非金属含有物を含む。この材料は、７００℃までまたはそれ以上までのターボ過給機の耐熱性を実現することを意図されている。   A heat-resistant material for exhaust gas turbochargers and their individual components is known from EP 1396620. In this document, a suitable material is considered a material having a certain composition, the surface of the component may be coated with a chromium carbide layer, and the material contains a small amount of small non-metal inclusions. This material is intended to achieve heat resistance of the turbocharger up to 700 ° C. or higher.

これに鑑みて、本発明の目的は、請求項１の前段に記載の保持ディスク、または請求項４の前段に記載のターボ過給機であって、極端な温度で、改良された耐温度性、耐酸化性、および耐食性を有し、また対応する耐湿食性も有し、最適なトライボロジー特性によって特徴付けられ、しかも摩耗しにくいターボ過給機を提供することである。   In view of this, an object of the present invention is a holding disk according to the first stage of claim 1 or a turbocharger according to the first stage of claim 4, wherein the temperature resistance is improved at an extreme temperature. It is to provide a turbocharger that has oxidation resistance and corrosion resistance and also has corresponding wet corrosion resistance, is characterized by optimal tribological properties and is also resistant to wear.

この目的は、請求項１および請求項４に記載の特徴によって実現される。   This object is achieved by the features of claims 1 and 4.

本発明による、オーステナイト鉄ベースの合金からなる保持ディスク、またはそのような保持ディスクを備える排気ガスターボ過給機の設計により、材料のより良い耐温度性が実現される。耐温度性は、鉄ベースの合金中に存在する樹枝状炭化物析出物、および窒素の含有によって何倍にも増加される。これにより、９００℃までの範囲内で最適な耐温度性を有し、耐高温性も非常に高く、高い耐摩耗性および耐食性を有し、さらに、酸化されにくい上に摺動特性が非常に良いことによって特徴付けられる本発明による保持ディスク、または保持ディスクを含む排気ガスターボ過給機が提供される。   By means of the design of a holding disk made of an austenitic iron-based alloy or an exhaust gas turbocharger comprising such a holding disk according to the invention, a better temperature resistance of the material is realized. Temperature resistance is increased many times by the inclusion of dendritic carbide precipitates and nitrogen present in the iron-based alloy. As a result, it has optimum temperature resistance within the range up to 900 ° C, very high temperature resistance, high wear resistance and corrosion resistance, and it is difficult to oxidize and has very good sliding characteristics. A holding disc according to the invention, characterized by the good, or an exhaust gas turbocharger comprising a holding disc is provided.

また、本発明による保持ディスクは、寸法安定性が高く、したがって非常に平坦である。   Also, the holding disc according to the invention has a high dimensional stability and is therefore very flat.

理論に拘束されずに、樹枝状での炭化物析出物は、支持効果を提供する微細な分枝を材料の微細構造内で形成することによって合金材料の安定性を高め、したがってその特別な構造により、材料の強度、したがって本発明による保持ディスクの強度をかなり高めると考えられる。   Without being bound by theory, dendritic carbide precipitates increase the stability of the alloy material by forming fine branches within the material's microstructure that provide a supporting effect and, therefore, due to its special structure. It is believed that the strength of the material and thus the strength of the holding disc according to the invention is considerably increased.

軸受荷重約１０Ｎ／ｍｍ２、摺動速度０．０２５ｍ／ｓ、構成要素温度５００〜９００℃、表面粗さＲｚ６．３、試験時間５００時間、クロック周波数０．２Ｈｚ、調節角度４５°、摩擦値０．２８、接触面積１０ｍｍ２、圧力脈動＜２００ｍｂａｒ、排気ガス圧＜１．５ｂａｒで、試験媒体としてディーゼル排気ガスを用いたとき、本発明による保持ディスクの最大摩耗率は０．０５ｍｍ未満である。 Bearing load about 10 N / mm 2 , sliding speed 0.025 m / s, component temperature 500 to 900 ° C., surface roughness Rz 6.3, test time 500 hours, clock frequency 0.2 Hz, adjustment angle 45 °, friction value 0.28, contact area 10 mm 2 , pressure pulsation <200 mbar, exhaust gas pressure <1.5 bar, and when using diesel exhaust gas as the test medium, the maximum wear rate of the holding disk according to the invention is less than 0.05 mm .

熱衝撃サイクル試験中、本発明による保持ディスクの材料の平坦性は、７０ｍｍの試験直径で０．１ｍｍ未満である。   During the thermal shock cycle test, the flatness of the material of the holding disk according to the invention is less than 0.1 mm with a test diameter of 70 mm.

従属請求項は、本発明の有利な発展形態を含む。   The dependent claims contain advantageous developments of the invention.

一実施形態では、本発明による保持ディスクは、以下の成分を含む特定の組成によって特徴付けられる。
Ｃ：０．１〜０．６重量％
Ｃｒ：２２〜２７重量％
Ｎｉ：６．５〜１５重量％
Ｍｎ：７．５〜１４．５重量％
Ｓｉ：≦１重量％
Ｖ：０．７５〜２．５重量％
Ｎ：０．１〜０．７重量％
および鉄。 In one embodiment, the holding disc according to the invention is characterized by a specific composition comprising the following components:
C: 0.1 to 0.6% by weight
Cr: 22-27% by weight
Ni: 6.5 to 15% by weight
Mn: 7.5 to 14.5% by weight
Si: ≦ 1% by weight
V: 0.75 to 2.5% by weight
N: 0.1 to 0.7% by weight
And iron.

鉄ベースの合金に対する個々の元素の影響は知られているが、ここで驚くべきことに、正確に上記の組合せにすると、保持ディスクを形成するために加工されるときに、特にバランスの取れた特性プロファイルを前記保持ディスクに与える材料が得られることが判明した。本発明によるこの組成物は、特に高い耐高温性および耐温度性（最大９００℃）を有し、優れた摺動特性、したがって特に低い摺動摩耗またはアブレシブ摩耗によって特徴付けられる保持ディスクを提供する。さらに、耐食性が最大になり、これは特に湿食にも当てはまる。さらに、本発明による材料、したがって保持ディスクは、非常に寸法安定性が高い。   The effects of individual elements on iron-based alloys are known, but surprisingly here, when precisely combined with the above, is particularly balanced when processed to form a retaining disk It has been found that a material is obtained which gives a characteristic profile to the holding disk. This composition according to the invention provides a retaining disk which has a particularly high high temperature resistance and temperature resistance (up to 900 ° C.) and is characterized by excellent sliding properties and thus particularly low sliding wear or abrasive wear. . Furthermore, the corrosion resistance is maximized, which is especially true for wet corrosion. Furthermore, the material according to the invention, and thus the holding disc, is very dimensionally stable.

したがって、このようにして製造される本発明による材料は、以下の特性を有する。   Thus, the material according to the invention produced in this way has the following properties:

Figure 2012503743
Figure 2012503743

本発明のさらなる実施形態によれば、本発明による保持ディスクは、シグマ相を含まない。これは、材料が脆性になるのを防止し、材料の耐久性を高める。シグマ相は、高硬度であり脆性の焼結金属の相である。この相は、原子半径の差がごくわずかである体心立方金属と面心立方金属の間で生じる。このタイプのシグマ相は、脆化効果をもち、またマトリックスがクロムを引き出す特性をもつため、望ましくない。したがって、本発明による材料は、シグマ相を含まないことによって特徴付けられる。これは、材料が脆性になるのを防止し、材料の耐久性を高める。シグマ相形成の減少または防止は、合金材料中のシリコン含有率を１．３重量％未満、好ましくは１重量％未満に減少することによって実現される。さらに、例えばマンガン、窒素、およびニッケル、適切であればそれらの組合せなど、オーステナイト形成元素を使用することが有利である。   According to a further embodiment of the invention, the holding disk according to the invention does not contain a sigma phase. This prevents the material from becoming brittle and increases the durability of the material. The sigma phase is a high hardness and brittle sintered metal phase. This phase occurs between body-centered and face-centered cubic metals with very little difference in atomic radii. This type of sigma phase is undesirable because it has a brittle effect and the matrix has the property of extracting chromium. The material according to the invention is therefore characterized by not containing a sigma phase. This prevents the material from becoming brittle and increases the durability of the material. Reduction or prevention of sigma phase formation is achieved by reducing the silicon content in the alloy material to less than 1.3 wt%, preferably less than 1 wt%. Furthermore, it is advantageous to use austenite-forming elements such as, for example, manganese, nitrogen and nickel, and combinations where appropriate.

別途に取り扱うことができる一目的として、請求項４は、樹枝状炭化物析出物を含むオーステナイトベースの構造からなる既述の保持ディスクを備える排気ガスターボ過給機を定義する。   As an object which can be handled separately, claim 4 defines an exhaust gas turbocharger comprising a retaining disk as described above which consists of an austenite-based structure containing dendritic carbide deposits.

本発明によるターボ過給機の斜視図を部分的に断面にして示す。1 is a partial cross-sectional view of a turbocharger according to the present invention.

図１は、本発明によるターボ過給機１を示し、このターボ過給機１は、タービンケーシング２と、軸受ケーシング２８を介してタービンケーシング２に接続されたコンプレッサケーシング３とを有する。ケーシング２、３、および２８は、回転軸Ｒに沿って配置されている。ブレード軸受リング６と半径方向外側のガイド火格子１８の構成を例示するために、タービンケーシングを部分的に断面で示してある。ガイド火格子１８は、前記リングによって形成され、複数の調節ブレード７を有し、これらのブレード７は、円周に沿って分布し、回転軸８を有する。このようにすると、形成されるノズル断面は、調節ブレード７の位置に依存して大きさが変わり、回転軸Ｒに心合わせされたタービンロータ４に対するエンジンからの排気ガスの作用の度合いも変わる。前記排気ガスは、供給管路９を通して供給され、中央接続部片１０を通して排出されて、タービンロータ４を使用して同じシャフト上に載置されたコンプレッサホイール１７を駆動する。   FIG. 1 shows a turbocharger 1 according to the present invention, which has a turbine casing 2 and a compressor casing 3 connected to the turbine casing 2 via a bearing casing 28. The casings 2, 3, and 28 are arranged along the rotation axis R. In order to illustrate the configuration of the blade bearing ring 6 and the radially outer guide grate 18, the turbine casing is shown partially in section. The guide grate 18 is formed by the ring and has a plurality of adjusting blades 7, which are distributed along the circumference and have a rotation axis 8. In this way, the size of the formed nozzle cross section changes depending on the position of the adjusting blade 7, and the degree of the action of the exhaust gas from the engine on the turbine rotor 4 centered on the rotation axis R also changes. The exhaust gas is supplied through a supply line 9 and discharged through a central connection piece 10 to drive a compressor wheel 17 mounted on the same shaft using the turbine rotor 4.

調節ブレード７の移動または位置を制御するために、作動デバイス１１が提供される。この作動デバイス１１は望みに応じて如何様にも設計することができるが、好ましい実施形態は制御ケーシング１２を有し、制御ケーシング１２は、そこに固定されたタペット部材１４の制御運動を制御して、ブレード軸受リング６の後方に位置された調節リング５に対する前記タペット部材の運動を前記調節リングのわずかな回転運動に変換する。調節ブレード７用の自由空間１３が、ブレード軸受リング６とタービンケーシング２の環状部分１５の間に形成される。この自由空間１３を保証することができるように、ブレード軸受リング６がスペーサ１６を有する。本発明によれば、タービンブレード７のための自由空間は、スペーサ６を用いて、保持ディスク１９によって上に向けて画定される。   In order to control the movement or position of the adjusting blade 7, an actuating device 11 is provided. The actuating device 11 can be designed in any way as desired, but a preferred embodiment has a control casing 12, which controls the control movement of the tappet member 14 secured thereto. Thus, the movement of the tappet member relative to the adjustment ring 5 located behind the blade bearing ring 6 is converted into a slight rotational movement of the adjustment ring. A free space 13 for the adjusting blade 7 is formed between the blade bearing ring 6 and the annular part 15 of the turbine casing 2. The blade bearing ring 6 has a spacer 16 so that this free space 13 can be guaranteed. According to the invention, the free space for the turbine blade 7 is defined upwards by the holding disk 19 using the spacer 6.

本発明による保持ディスクを形成するための合金を、従来のプロセスによって以下の元素から製造した。化学的分析により、各元素に関して以下の値が得られた。Ｃ：０．１〜０．５重量％、Ｃｒ：２３〜２６重量％、Ｎｉ：６．５〜１２．５重量％、Ｍｎ：７．５〜１２重量％、Ｓｉ：最大１重量％、Ｎｂ：０．７５〜１．７重量％、Ｎ：０．１〜０．５重量％、Ｖ：０．８〜１．７重量％、残部：鉄。   An alloy for forming a holding disk according to the present invention was produced from the following elements by conventional processes. The following values were obtained for each element by chemical analysis. C: 0.1 to 0.5 wt%, Cr: 23 to 26 wt%, Ni: 6.5 to 12.5 wt%, Mn: 7.5 to 12 wt%, Si: maximum 1 wt%, Nb : 0.75 to 1.7 wt%, N: 0.1 to 0.5 wt%, V: 0.8 to 1.7 wt%, balance: iron.

この実施例に従って製造した調節リングは、６６８ＭＰａの引張り強度Ｒｍによって特徴付けられた（ＡＳＴＭ Ｅ ８Ｍ／ＥＮ １０００２−１、高温ではＥＮ １０００２−５）。降伏強度Ｒｐ０．２（標準のプロセスを使用して測定）は、３８４Ｍｐａであった。材料の破断伸び（標準のプロセスを使用して測定）は、１３．１％であった。材料の硬度（ＡＳＴＭ Ｅ ９２／ＩＳＯ ６５０７−１に従って測定）は、２０７ＨＢであった。線膨張率（標準のプロセスを使用して測定）は、１６．９Ｋ−１であった（２０〜９００℃）。材料を、以下の試験を含む妥当性検査シリーズにかけた。
−屋外風化試験
−気候変動試験
−熱衝撃試験／サイクル試験−３００時間
−分解炉内での高温ガス腐食試験 The adjustment ring produced according to this example was characterized by a tensile strength R m of 668 MPa (ASTM E 8M / EN 10002-1, EN 10002-5 at high temperature). The yield strength R p 0.2 (measured using a standard process) was 384 Mpa. The material elongation at break (measured using a standard process) was 13.1%. The hardness of the material (measured according to ASTM E 92 / ISO 6507-1) was 207 HB. The coefficient of linear expansion (measured using a standard process) was 16.9 K −1 (20-900 ° C.). The material was subjected to a validation series that included the following tests.
-Outdoor weathering test-Climate change test-Thermal shock test / cycle test-300 hours-Hot gas corrosion test in cracking furnace

すべての試験において、構成要素は、作用する力に対する優れた耐性によって特徴付けられた。したがって、この材料は、非常に高い耐摩耗性および優れた耐酸化性を有し、それにより、上記の条件下での材料に対する腐食または摩耗がかなり低減され、したがって材料の耐性も長期保証された。   In all tests, the component was characterized by excellent resistance to acting forces. Therefore, this material has a very high wear resistance and excellent oxidation resistance, thereby significantly reducing the corrosion or wear on the material under the above conditions and thus also guaranteeing the durability of the material for a long time .

熱サイクル試験：
本発明による構成要素を熱サイクル試験にかけた。この試験では、以下のように熱衝撃試験を行った。
１．固定ロータの使用
２．２−ＥＧＴ操作
３．試験時間：３５０時間（約２０００サイクル）
４．試験中、ＥＧＴの排気ガスフラップは１５°で開けたままにする
５．高温：公称馬力点Ｔ３＝７５０℃、タービン側での質量流量ＥＧＴ：０．５ｋｇ／ｓ
６．低温：Ｔ３＝１００℃、タービン側での質量流量ＥＧＴ：０．５ｋｇ／ｓ
７．サイクル時間：２×５分（１０分）
８．３回の中間亀裂試験を行う Thermal cycle test:
The component according to the invention was subjected to a thermal cycle test. In this test, a thermal shock test was performed as follows.
1. Use of fixed rotor 2.2-EGT operation Test time: 350 hours (approximately 2000 cycles)
4). 4. During the test, leave the EGT exhaust flap open at 15 °. High temperature: nominal horsepower point T3 = 750 ° C., mass flow rate EGT on turbine side: 0.5 kg / s
6). Low temperature: T3 = 100 ° C., mass flow rate EGT on the turbine side: 0.5 kg / s
7). Cycle time: 2 x 5 minutes (10 minutes)
8. Perform three intermediate crack tests

１ ターボ過給機
２ タービンケーシング
３ コンプレッサケーシング
４ タービンロータ
５ 調節リング
６ ブレード軸受リング
７ 調節ブレード
８ 回転軸
９ 供給管路
１０ 軸方向接続部片
１１ 作動デバイス
１２ 制御ケーシング
１３ 調節ブレード７用の自由空間
１４ タペット部材
１５ タービンケーシング２の環状部分
１６ スペーサ／スペーサボス
１７ コンプレッサホイール
１８ ガイド火格子
１９ 保持ディスク
２８ 軸受ケーシング
Ｒ 回転軸 DESCRIPTION OF SYMBOLS 1 Turbocharger 2 Turbine casing 3 Compressor casing 4 Turbine rotor 5 Adjustment ring 6 Blade bearing ring 7 Adjustment blade 8 Rotating shaft 9 Supply line 10 Axial connection piece 11 Actuation device 12 Control casing 13 Free for adjustment blade 7 Space 14 Tappet member 15 Annular portion of turbine casing 2 16 Spacer / spacer boss 17 Compressor wheel 18 Guide grate 19 Holding disk 28 Bearing casing R Rotating shaft

Claims (6)

特にディーゼルエンジン用のターボ過給機で使用するための保持ディスクであって、樹枝状炭化物析出物を含むオーステナイトベースの構造を有する鉄ベースの合金からなる保持ディスク。   A holding disk for use in a turbocharger, in particular for a diesel engine, comprising an iron-based alloy having an austenite-based structure containing dendritic carbide deposits. 成分として、
Ｃ：０．１〜０．６重量％、Ｃｒ：２２〜２７重量％、Ｎｉ：６．５〜１５重量％、Ｍｎ：７．５〜１４．５重量％、Ｓｉ：≦１重量％、Ｖ：０．７５〜２．５重量％、Ｎ：０．１〜０．７重量％、およびＦｅ
を含む請求項１に記載の保持ディスク。 As an ingredient
C: 0.1 to 0.6 wt%, Cr: 22 to 27 wt%, Ni: 6.5 to 15 wt%, Mn: 7.5 to 14.5 wt%, Si: ≤ 1 wt%, V : 0.75 to 2.5 wt%, N: 0.1 to 0.7 wt%, and Fe
The holding disk according to claim 1, comprising: シグマ相を含まない請求項１に記載の保持ディスク。   The holding disk according to claim 1, which does not contain a sigma phase. ディーゼルエンジン用の排気ガスターボ過給機であって、樹枝状炭化物析出物を含むオーステナイトベースの構造からなる保持ディスクを備える排気ガスターボ過給機。   An exhaust gas turbocharger for a diesel engine, comprising an austenite-based holding disk comprising dendritic carbide deposits. 前記保持ディスクが、成分として、
Ｃ：０．１〜０．６重量％、Ｃｒ：２２〜２７重量％、Ｎｉ：６．５〜１５重量％、Ｍｎ：７．５〜１４．５重量％、Ｓｉ：≦１重量％、Ｖ：０．７５〜２．５重量％、Ｎ：０．１〜０．７重量％、およびＦｅ
を含む請求項４に記載の排気ガスターボ過給機。 The holding disk as a component,
C: 0.1 to 0.6 wt%, Cr: 22 to 27 wt%, Ni: 6.5 to 15 wt%, Mn: 7.5 to 14.5 wt%, Si: ≤ 1 wt%, V : 0.75 to 2.5 wt%, N: 0.1 to 0.7 wt%, and Fe
The exhaust gas turbocharger according to claim 4. 前記保持ディスクの材料がシグマ相を含まない請求項４に記載の排気ガスターボ過給機。   The exhaust gas turbocharger according to claim 4, wherein the material of the holding disk does not contain a sigma phase.
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Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103534374B (en) * 2011-05-19 2016-04-06 博格华纳公司 Austenite ferrous alloy, the turbo-supercharger be made up of it and parts
DE112012003677T5 (en) * 2011-10-20 2014-06-26 Borgwarner Inc. Turbocharger and a component for this
US9896752B2 (en) 2014-07-31 2018-02-20 Honeywell International Inc. Stainless steel alloys, turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same
US9534281B2 (en) 2014-07-31 2017-01-03 Honeywell International Inc. Turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same
US10316694B2 (en) 2014-07-31 2019-06-11 Garrett Transportation I Inc. Stainless steel alloys, turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same
DE102020202736A1 (en) 2020-03-04 2021-09-09 Mahle International Gmbh Metallic material

Citations (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS491423A (en) * 1972-04-24 1974-01-08
JPS51133807A (en) * 1975-05-14 1976-11-19 Hitachi Ltd Turbo type impeller with high performance
JPS6043473A (en) * 1983-06-10 1985-03-08 サントレード　リミティド Anticorrosive chromium-nickel-manganese-iron alloy
US4560408A (en) * 1983-06-10 1985-12-24 Santrade Limited Method of using chromium-nickel-manganese-iron alloy with austenitic structure in sulphurous environment at high temperature
US4711677A (en) * 1986-07-18 1987-12-08 The Garrett Corporation High temperature bushing alloy
WO1991016467A1 (en) * 1990-04-16 1991-10-31 Carondelet Foundry Company Heat resistant alloys
JPH055161A (en) * 1990-08-02 1993-01-14 Hitachi Metals Ltd Austenitic heat resistant cast steel excellent in high temperature strength and exhaust system part made thereof
US5201965A (en) * 1991-04-15 1993-04-13 Hitachi Metals, Ltd. Heat-resistant cast steel, method of producing same, and exhaust equipment member made thereof
JPH08319504A (en) * 1995-03-17 1996-12-03 Toyota Motor Corp Composite material of metallic sintered compact and its production
US5582657A (en) * 1993-11-25 1996-12-10 Hitachi Metals, Ltd. Heat-resistant, ferritic cast steel having high castability and exhaust equipment member made thereof
JPH1053832A (en) * 1996-08-07 1998-02-24 Hokkaido Prefecture Wc-iron alloy, containing iron-carbon as binding material, and its production
JPH10220236A (en) * 1997-02-12 1998-08-18 Daido Steel Co Ltd Tial made turbine rotor
JP2002194511A (en) * 2000-12-14 2002-07-10 Caterpillar Inc Heat resistant and corrosion resistant cast stainless steel having superior high temperature strength and ductility
JP2002332553A (en) * 2001-05-10 2002-11-22 Sogi Kogyo Kk Exhaust guide assembly of vgs type turbocharger consisting of member with rare earth element or the like added and having improved high temperature durability
JP2004269979A (en) * 2003-03-10 2004-09-30 Toyota Central Res & Dev Lab Inc Heat resistant cast steel, heat resistant member made of cast steel, and production method therefor
JP2004339562A (en) * 2003-05-15 2004-12-02 Air Water Inc Method for surface-reforming austenitic metal, refractory metal product and turbo-component obtained thereby
JP2005248263A (en) * 2004-03-04 2005-09-15 Daido Steel Co Ltd Martensitic stainless steel
WO2006010383A1 (en) * 2004-07-30 2006-02-02 Honeywell International Inc. Turbocharger component
US20070217941A1 (en) * 2004-04-19 2007-09-20 Hitachi Metals, Ltd HIGH-Cr HIGH-Ni, HEAT-RESISTANT, AUSTENITIC CAST STEEL AND EXHAUST EQUIPMENT MEMBERS FORMED THEREBY
WO2008018128A1 (en) * 2006-08-09 2008-02-14 Ing Shoji Co., Ltd. Iron-based corrosion resistant wear resistant alloy and deposit welding material for obtaining the alloy
JP2009545675A (en) * 2006-07-31 2009-12-24 キャタピラー インコーポレイテッド Heat and corrosion resistant austenitic stainless steel cast steel alloy with improved high temperature strength

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6007301A (en) * 1996-10-18 1999-12-28 Diado Steel Co., Ltd. TiAl turbine rotor and method of manufacturing
EP1396620A4 (en) 2001-05-10 2005-01-12 Soghi Kogyo Co Ltd Exhaust guide assembly for vgs type turbo charger improved in heat resistance and method of producing heat-resisting members applicable thereto, and method of producing raw material for variable vanes applicable thereto
US20060065327A1 (en) * 2003-02-07 2006-03-30 Advance Steel Technology Fine-grained martensitic stainless steel and method thereof
US20080145264A1 (en) * 2006-12-19 2008-06-19 The Timken Company Mo-V-Ni high temperature steels, articles made therefrom and method of making

Patent Citations (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS491423A (en) * 1972-04-24 1974-01-08
JPS51133807A (en) * 1975-05-14 1976-11-19 Hitachi Ltd Turbo type impeller with high performance
JPS6043473A (en) * 1983-06-10 1985-03-08 サントレード　リミティド Anticorrosive chromium-nickel-manganese-iron alloy
US4560408A (en) * 1983-06-10 1985-12-24 Santrade Limited Method of using chromium-nickel-manganese-iron alloy with austenitic structure in sulphurous environment at high temperature
US4711677A (en) * 1986-07-18 1987-12-08 The Garrett Corporation High temperature bushing alloy
WO1991016467A1 (en) * 1990-04-16 1991-10-31 Carondelet Foundry Company Heat resistant alloys
JPH055161A (en) * 1990-08-02 1993-01-14 Hitachi Metals Ltd Austenitic heat resistant cast steel excellent in high temperature strength and exhaust system part made thereof
US5201965A (en) * 1991-04-15 1993-04-13 Hitachi Metals, Ltd. Heat-resistant cast steel, method of producing same, and exhaust equipment member made thereof
US5582657A (en) * 1993-11-25 1996-12-10 Hitachi Metals, Ltd. Heat-resistant, ferritic cast steel having high castability and exhaust equipment member made thereof
JPH08319504A (en) * 1995-03-17 1996-12-03 Toyota Motor Corp Composite material of metallic sintered compact and its production
JPH1053832A (en) * 1996-08-07 1998-02-24 Hokkaido Prefecture Wc-iron alloy, containing iron-carbon as binding material, and its production
JPH10220236A (en) * 1997-02-12 1998-08-18 Daido Steel Co Ltd Tial made turbine rotor
JP2002194511A (en) * 2000-12-14 2002-07-10 Caterpillar Inc Heat resistant and corrosion resistant cast stainless steel having superior high temperature strength and ductility
JP2002332553A (en) * 2001-05-10 2002-11-22 Sogi Kogyo Kk Exhaust guide assembly of vgs type turbocharger consisting of member with rare earth element or the like added and having improved high temperature durability
JP2004269979A (en) * 2003-03-10 2004-09-30 Toyota Central Res & Dev Lab Inc Heat resistant cast steel, heat resistant member made of cast steel, and production method therefor
JP2004339562A (en) * 2003-05-15 2004-12-02 Air Water Inc Method for surface-reforming austenitic metal, refractory metal product and turbo-component obtained thereby
JP2005248263A (en) * 2004-03-04 2005-09-15 Daido Steel Co Ltd Martensitic stainless steel
US20070217941A1 (en) * 2004-04-19 2007-09-20 Hitachi Metals, Ltd HIGH-Cr HIGH-Ni, HEAT-RESISTANT, AUSTENITIC CAST STEEL AND EXHAUST EQUIPMENT MEMBERS FORMED THEREBY
WO2006010383A1 (en) * 2004-07-30 2006-02-02 Honeywell International Inc. Turbocharger component
JP2009545675A (en) * 2006-07-31 2009-12-24 キャタピラー インコーポレイテッド Heat and corrosion resistant austenitic stainless steel cast steel alloy with improved high temperature strength
WO2008018128A1 (en) * 2006-08-09 2008-02-14 Ing Shoji Co., Ltd. Iron-based corrosion resistant wear resistant alloy and deposit welding material for obtaining the alloy

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