JP2002332851A - Exhaust guide assembly for vgs turbocharger with improved durability composed of superalloy - Google Patents
Exhaust guide assembly for vgs turbocharger with improved durability composed of superalloyInfo
- Publication number
- JP2002332851A JP2002332851A JP2001140116A JP2001140116A JP2002332851A JP 2002332851 A JP2002332851 A JP 2002332851A JP 2001140116 A JP2001140116 A JP 2001140116A JP 2001140116 A JP2001140116 A JP 2001140116A JP 2002332851 A JP2002332851 A JP 2002332851A
- Authority
- JP
- Japan
- Prior art keywords
- exhaust
- carbide
- guide assembly
- variable
- exhaust guide
- 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
- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 15
- 229910039444 MoC Inorganic materials 0.000 claims abstract description 7
- INZDTEICWPZYJM-UHFFFAOYSA-N 1-(chloromethyl)-4-[4-(chloromethyl)phenyl]benzene Chemical compound C1=CC(CCl)=CC=C1C1=CC=C(CCl)C=C1 INZDTEICWPZYJM-UHFFFAOYSA-N 0.000 claims abstract description 5
- QIJNJJZPYXGIQM-UHFFFAOYSA-N 1lambda4,2lambda4-dimolybdacyclopropa-1,2,3-triene Chemical compound [Mo]=C=[Mo] QIJNJJZPYXGIQM-UHFFFAOYSA-N 0.000 claims abstract description 5
- UNASZPQZIFZUSI-UHFFFAOYSA-N methylidyneniobium Chemical compound [Nb]#C UNASZPQZIFZUSI-UHFFFAOYSA-N 0.000 claims abstract description 5
- 229910003470 tongbaite Inorganic materials 0.000 claims abstract description 5
- MTPVUVINMAGMJL-UHFFFAOYSA-N trimethyl(1,1,2,2,2-pentafluoroethyl)silane Chemical compound C[Si](C)(C)C(F)(F)C(F)(F)F MTPVUVINMAGMJL-UHFFFAOYSA-N 0.000 claims abstract description 5
- UONOETXJSWQNOL-UHFFFAOYSA-N tungsten carbide Chemical compound [W+]#[C-] UONOETXJSWQNOL-UHFFFAOYSA-N 0.000 claims abstract description 4
- UFGZSIPAQKLCGR-UHFFFAOYSA-N chromium carbide Chemical compound [Cr]#C[Cr]C#[Cr] UFGZSIPAQKLCGR-UHFFFAOYSA-N 0.000 claims abstract 2
- 230000002093 peripheral effect Effects 0.000 claims description 5
- 229910045601 alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 239000000470 constituent Substances 0.000 abstract 1
- 230000003647 oxidation Effects 0.000 abstract 1
- 238000007254 oxidation reaction Methods 0.000 abstract 1
- 230000005540 biological transmission Effects 0.000 description 5
- 239000011651 chromium Substances 0.000 description 4
- 230000006866 deterioration Effects 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- GVEHJMMRQRRJPM-UHFFFAOYSA-N chromium(2+);methanidylidynechromium Chemical compound [Cr+2].[Cr]#[C-].[Cr]#[C-] GVEHJMMRQRRJPM-UHFFFAOYSA-N 0.000 description 3
- 239000011248 coating agent Substances 0.000 description 3
- 238000000576 coating method Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000001629 suppression Effects 0.000 description 3
- 229910001293 incoloy Inorganic materials 0.000 description 2
- 229910001026 inconel Inorganic materials 0.000 description 2
- 238000005121 nitriding Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- 229910052721 tungsten Inorganic materials 0.000 description 2
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- 101100219325 Phaseolus vulgaris BA13 gene Proteins 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 238000005255 carburizing Methods 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000002788 crimping Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000001747 exhibiting effect Effects 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 239000003779 heat-resistant material Substances 0.000 description 1
- 238000007654 immersion Methods 0.000 description 1
- 238000005495 investment casting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 239000011733 molybdenum Substances 0.000 description 1
- 238000006386 neutralization reaction Methods 0.000 description 1
- 229910052758 niobium Inorganic materials 0.000 description 1
- 239000010955 niobium Substances 0.000 description 1
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 150000003839 salts Chemical class 0.000 description 1
- 238000007528 sand casting Methods 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
- 229910052720 vanadium Inorganic materials 0.000 description 1
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Supercharger (AREA)
- Control Of Turbines (AREA)
- Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は自動車用エンジン等
に用いられるターボチャージャに関するものであって、
特にこのものに組み込まれる排気ガイドアッセンブリに
係るものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbocharger used for an automobile engine and the like.
In particular, the present invention relates to an exhaust guide assembly incorporated therein.
【０００２】[0002]
【発明の背景】自動車用エンジンの高出力化、高性能化
の一手段として用いられる過給機としてターボチャージ
ャが知られており、このものはエンジンの排気エネルギ
によってタービンを駆動し、このタービンの出力によっ
てコンプレッサを回転させ、エンジンに自然吸気以上の
過給状態をもたらす装置である。ところでこのターボチ
ャージャは、エンジンが低速回転しているときには、排
気流量の低下により排気タービンが効率的に回るまでの
もたつき感と、その後の一挙に吹き上がるまでの所要時
間いわゆるターボラグ等が生ずることを免れないもので
あった。またもともとエンジン回転が低いディーゼルエ
ンジンでは、ターボ効果を得にくいという欠点があっ
た。2. Description of the Related Art A turbocharger is known as a supercharger used as a means for increasing the output and performance of an automobile engine. This turbocharger drives a turbine by the exhaust energy of the engine. This is a device that rotates the compressor by the output to bring the engine to a supercharged state that is higher than natural intake. By the way, this turbocharger has a problem that when the engine is running at a low speed, there is a feeling of sluggishness until the exhaust turbine rotates efficiently due to a decrease in the exhaust flow rate, and a so-called turbo lag or the like, which is a necessary time until the exhaust is blown all at once. It was unavoidable. Also, a diesel engine having a low engine speed originally had a disadvantage that it was difficult to obtain a turbo effect.
【０００３】このため低速回転域からでも効率的に作動
するＶＧＳタイプのターボチャージャが開発されてきて
いる。このものは少ない排気量を可変翼（羽）で絞り込
み、排気の速度を増し、排気タービンの仕事量を大きく
することで、低速回転時でも高出力を発揮できるように
したものであり、特に近年その排気ガス中のＮＯｘ量が
問題とされているディーゼルエンジンにおいては、低速
回転時からエンジンの効率化を図ることのできる有用な
ターボチャージャである。このＶＧＳタイプのターボチ
ャージャにおける排気ガイドアッセンブリは高温・排気
ガス雰囲気下で使用されるものであり、その製造には、
耐熱性を有する素材、例えばＪＩＳ規格、ＳＵＳ、ＳＵ
Ｈ、ＳＣＨ、ＮＣＦ超合金等の耐熱材料が使用されてい
るが、非常に過酷な条件で使用されるものであるため、
その耐久寿命には、一定の限界があり、更なる耐久性の
向上が切望されている。For this reason, a VGS type turbocharger which operates efficiently even in a low speed rotation range has been developed. This engine is capable of exhibiting high output even at low rotation speeds by narrowing a small amount of exhaust with variable blades (blades), increasing the exhaust speed, and increasing the work of the exhaust turbine. In a diesel engine in which the amount of NOx in the exhaust gas is a problem, the turbocharger is a useful turbocharger that can improve the efficiency of the engine from a low speed rotation. The exhaust guide assembly in this VGS type turbocharger is used under a high temperature and exhaust gas atmosphere.
Materials with heat resistance, such as JIS, SUS, SU
Although heat-resistant materials such as H, SCH, and NCF superalloys are used, since they are used under extremely severe conditions,
The durable life has a certain limit, and further improvement in durability is desired.
【０００４】[0004]
【開発を試みた技術的課題】本発明はこのような背景を
認識してなされたものであって、最高１０００℃にも達
する熱サイクル、排気ガス雰囲気下で長時間使用される
ことにより生ずる、排気ガイドアッセンブリを構成する
部材の高温摺動による摩耗劣化の抑制と、高温強度の持
続性向上とを試みたものである。SUMMARY OF THE INVENTION The present invention has been made in view of such a background, and has been achieved by a heat cycle reaching a maximum of 1000 ° C. and a prolonged use in an exhaust gas atmosphere. An attempt was made to suppress wear deterioration due to high-temperature sliding of members constituting the exhaust guide assembly and to improve sustainability of high-temperature strength.
【０００５】[0005]
【課題を解決するための手段】すなわち請求項１記載の
超合金により構成される耐久性を向上させたＶＧＳタイ
プターボチャージャの排気ガイドアッセンブリは、エン
ジンから排出される排気ガスの流量を適宜調節して排気
タービンを回転させる可変翼と、この可変翼を排気ター
ビンの外周部において回動自在に支持するタービンフレ
ームと、この可変翼を適宜回動させ、排気ガスの流量を
調節する可変機構とを具え、少ない排気流量を可変翼に
よって絞り込み、排気の速度を増し、低速回転時にも高
出力を発揮できるようにしたＶＧＳタイプのターボチャ
ージャにおける排気ガイドアッセンブリにおいて、前記
排気ガイドアッセンブリを構成する耐熱部材が、超合金
であることを特徴として成るものである。According to a first aspect of the present invention, there is provided an exhaust guide assembly of a VGS type turbocharger comprising a superalloy and having improved durability, wherein the flow rate of exhaust gas discharged from an engine is appropriately adjusted. Blades for rotating the exhaust turbine, a turbine frame for rotatably supporting the variable blades on the outer periphery of the exhaust turbine, and a variable mechanism for adjusting the flow rate of exhaust gas by appropriately rotating the variable blades. In the exhaust guide assembly of the VGS type turbocharger in which a small exhaust flow rate is narrowed down by the variable blade to increase the exhaust speed and exhibit a high output even at low speed rotation, a heat-resistant member constituting the exhaust guide assembly is provided. , A superalloy.
【０００６】また請求項２記載の超合金により構成され
る耐久性を向上させたＶＧＳタイプターボチャージャの
排気ガイドアッセンブリは、前記請求項１記載の要件に
加え、前記排気ガイドアッセンブリを構成する請求項１
記載の耐熱部材の表面を、クロム炭化物、チタン炭化
物、タングステン炭化物、バナジウム炭化物、ニオブ炭
化物またはモリブデン炭化物で被膜することを特徴とし
て成るものである。[0006] An exhaust guide assembly of a VGS type turbocharger made of a superalloy according to claim 2 and having improved durability, in addition to the requirements of claim 1, constitutes the exhaust guide assembly. 1
The surface of the heat resistant member described above is characterized by being coated with chromium carbide, titanium carbide, tungsten carbide, vanadium carbide, niobium carbide or molybdenum carbide.
【０００７】ここで被膜成分のクロム炭化物としては、
Cr23C6、Cr7C3 、Cr3C2 等があり、特に成膜性、高温摩
耗性の点で、Cr7C3 が好ましく、チタン炭化物として
は、TiC 、Ti2C等があり、特に被膜性、高温摩耗性の点
で、TiC が好ましく、タングステン炭化物としては、W
C、W2C 等があり、特に成膜性、高温摩耗性の点で、WC
等が好ましく、モリブデン炭化物としては、MoC 、Mo2C
等があり、特に成膜性、高温摩耗性の点でMoC が好まし
い。またバナジウム炭化物、ニオブ炭化物としては、そ
れぞれＶＣ及びＮｂＣが望ましい。Here, as the chromium carbide as a coating component,
There are Cr 23 C 6 , Cr 7 C 3 , Cr 3 C 2 and the like, and in particular, Cr 7 C 3 is preferable in terms of film formability and high-temperature abrasion, and as the titanium carbide, there is TiC, Ti 2 C, etc. In particular, TiC is preferable in terms of film properties and high-temperature wear properties.
C, W 2 C, etc.
And the like, and the molybdenum carbide is MoC, Mo 2 C
MoC is particularly preferred from the viewpoints of film forming properties and high-temperature wear properties. As the vanadium carbide and the niobium carbide, VC and NbC are desirable, respectively.
【０００８】また超合金とは、７００〜１０５０℃で使
用される耐熱合金であり、具体的には、Incoloy 800H、
Incoloy825、Inconel 713C、IN-100、MAR-M 246 、Hast
eloyS、等を挙げることができる。[0008] A superalloy is a heat-resistant alloy used at 700 to 1050 ° C, and specifically, Incoloy 800H,
Incoloy825, Inconel 713C, IN-100, MAR-M246, Hast
eloyS, and the like.
【０００９】[0009]
【発明の実施の形態】以下本発明について具体的に説明
する。説明にあたっては、本発明に係るＶＧＳタイプの
ターボチャージャにおける排気ガイドアッセンブリにつ
いて説明し、その後、排気ガイドアッセンブリＡを構成
する耐熱部材の製造及び当該耐熱部材を使用した当該排
気アッセンブリの製造等について説明する。BEST MODE FOR CARRYING OUT THE INVENTION The present invention will be specifically described below. In the description, the exhaust guide assembly in the VGS type turbocharger according to the present invention will be described, and then the manufacture of a heat-resistant member constituting the exhaust guide assembly A and the manufacture of the exhaust assembly using the heat-resistant member will be described. .
【００１０】〔１〕排気ガイドアッセンブリ 排気ガイドアッセンブリＡは、特にエンジンの低速回転
時において排気ガスＧを適宜絞り込んで排気流量を調節
するものであり、一例として図１に示すように、排気タ
ービンＴの外周に設けられた実質的に排気流量を設定す
る複数の可変翼１と、可変翼１を回動自在に保持するタ
ービンフレーム２と、排気ガスＧの流量を適宜設定すべ
く可変翼１を一定角度回動させる可変機構３とを具えて
成るものである。[1] Exhaust guide assembly The exhaust guide assembly A adjusts the exhaust gas flow by appropriately restricting the exhaust gas G particularly at the time of low-speed rotation of the engine. As an example, as shown in FIG. A plurality of variable blades 1 provided on the outer periphery of the turbine for substantially setting the exhaust flow rate, a turbine frame 2 for rotatably holding the variable blades 1, and a variable blade 1 for appropriately setting the flow rate of the exhaust gas G. And a variable mechanism 3 for rotating by a fixed angle.
【００１１】まず可変翼１について説明する。このもの
は一例として図１に示すように排気タービンＴの外周に
沿って円弧状に複数（一基の排気ガイドアッセンブリＡ
に対して概ね１０個から１５個程度）配設され、そのそ
れぞれが、ほぼ同程度づつ回動して排気流量を適宜調節
するものである。そして各可変翼１は、翼部１１と、軸
部１２とを具えて成る。翼部１１は、主に排気タービン
Ｔの幅寸法に応じて一定幅を有するように形成されるも
のであり、その幅方向における断面が概ね翼状に形成さ
れ、排気ガスＧが効果的に排気タービンＴに向かうよう
に構成されている。なおここで翼部１１の幅寸法を便宜
上、羽根高さｈとする。軸部１２は、翼部１１と一体で
連続するように形成されるものであり、翼部１１を動か
す際の回動軸に相当する部位となる。First, the variable wing 1 will be described. As an example, as shown in FIG. 1, a plurality of (one exhaust guide assembly A) is formed in an arc shape along the outer periphery of the exhaust turbine T.
, And each of them is rotated by approximately the same amount to adjust the exhaust flow rate appropriately. Each variable wing 1 includes a wing 11 and a shaft 12. The wing portion 11 is formed so as to have a constant width mainly in accordance with the width dimension of the exhaust turbine T, and has a substantially wing-shaped cross section in the width direction, so that the exhaust gas G can be effectively discharged from the exhaust turbine T. It is configured to face T. Here, the width of the wing portion 11 is referred to as a blade height h for convenience. The shaft portion 12 is formed so as to be continuous with the wing portion 11 integrally, and serves as a portion corresponding to a rotation axis when the wing portion 11 is moved.
【００１２】また翼部１１と軸部１２との接続部位に
は、軸部１２から翼部１１に向かって窄まるようなテー
パ部１３と、軸部１２より幾分大径の鍔部１４とが連な
るように形成されている。なお鍔部１４の底面は、翼部
１１の軸部１２側の端面と、ほぼ同一平面上に形成さ
れ、この平面によって、可変翼１をタービンフレーム２
に取り付けた状態において円滑な回動状態を確保してい
る。更に軸部１２の先端部には、可変翼１の取付状態の
基準となる基準面１５が形成される。この基準面１５
は、後述する可変機構３に対しカシメ等によって固定さ
れる部位であり、一例として図１に示すように、軸部１
２を対向的に切り欠いた平面が、翼部１１に対してほぼ
一定の傾斜状態に形成されて成るものである。A connecting portion between the wing portion 11 and the shaft portion 12 includes a tapered portion 13 narrowing from the shaft portion 12 toward the wing portion 11 and a flange portion 14 having a diameter somewhat larger than that of the shaft portion 12. Are formed so as to be continuous. The bottom surface of the flange portion 14 is formed on substantially the same plane as the end surface of the blade portion 11 on the shaft portion 12 side.
In this state, a smooth rotation is ensured in a state in which it is attached to the camera. Further, a reference surface 15 which is a reference of the mounted state of the variable wing 1 is formed at the tip of the shaft portion 12. This reference plane 15
Is a portion fixed by caulking or the like to a variable mechanism 3 described later. As an example, as shown in FIG.
2 is formed so that a flat surface which is notched opposite to the wing portion 11 is formed in a substantially constant inclined state with respect to the wing portion 11.
【００１３】次に本発明を実質的に適用したタービンフ
レーム２について説明する。このものは、複数の可変翼
１を回動自在に保持するフレーム部材として構成される
ものであって、一例として図１に示すように、フレーム
セグメント２１と保持部材２２とによって可変翼１を挟
み込むように構成される。そしてフレームセグメント２
１は、可変翼１の軸部１２を受け入れるフランジ部２３
と、後述する可変機構３を外周に嵌めるボス部２４とを
具えて成る。なおこのような構造からフランジ部２３に
は、周縁部分に可変翼１と同数の受入孔２５が等間隔で
形成されるものであり、本発明では特に、この受入孔２
５を高効率に形成し、また高精度に仕上げるものであ
る。このため本発明の実質的な適用対象物は、フレーム
セグメント２１となる。Next, a description will be given of a turbine frame 2 to which the present invention is substantially applied. This is configured as a frame member that rotatably holds a plurality of variable wings 1, and as an example, as shown in FIG. 1, the variable wing 1 is sandwiched between a frame segment 21 and a holding member 22. It is configured as follows. And frame segment 2
1 is a flange portion 23 for receiving the shaft portion 12 of the variable wing 1
And a boss 24 for fitting a variable mechanism 3 to be described later on the outer periphery. It should be noted that the same number of receiving holes 25 as the number of the variable wings 1 are formed at equal intervals in the peripheral portion of the flange portion 23 from such a structure.
5 is formed with high efficiency and finished with high precision. Therefore, the substantial application object of the present invention is the frame segment 21.
【００１４】また保持部材２２は、図１に示すように中
央部分が開口された円板状に形成されている。そしてこ
れらフレームセグメント２１と保持部材２２とによって
挟み込まれた可変翼１の翼部１１を、常に円滑に回動さ
せ得るように、両部材間の寸法は、ほぼ一定（概ね可変
翼１の翼幅寸法程度）に維持されるものであり、一例と
して受入孔２５の外周部分に、四カ所設けられたカシメ
ピン２６によって両部材間の寸法が維持されている。こ
こで上記カシメピン２６を受け入れるためにフレームセ
グメント２１及び保持部材２２に開口される孔をピン孔
２７とする。Further, as shown in FIG. 1, the holding member 22 is formed in a disk shape having a central portion opened. The dimension between the two members is substantially constant (generally the wing width of the variable wing 1) so that the wing portion 11 of the variable wing 1 sandwiched between the frame segment 21 and the holding member 22 can be always smoothly rotated. For example, the dimensions between the two members are maintained by crimping pins 26 provided at four positions on the outer peripheral portion of the receiving hole 25. Here, a hole opened in the frame segment 21 and the holding member 22 for receiving the caulking pin 26 is referred to as a pin hole 27.
【００１５】なおこの実施の形態では、フレームセグメ
ント２１のフランジ部２３は、保持部材２２とほぼ同径
のフランジ部２３Ａと、保持部材２２より幾分大きい径
のフランジ部２３Ｂとの二つのフランジ部分から成るも
のであり、これらを同一部材で形成するものであるが、
同一部材での加工が複雑になる場合等にあっては、径の
異なる二つのフランジ部を分割して形成し、後にカシメ
加工やブレージング加工等によって接合することも可能
である。In this embodiment, the flange portion 23 of the frame segment 21 has two flange portions: a flange portion 23A having substantially the same diameter as the holding member 22 and a flange portion 23B having a diameter somewhat larger than the holding member 22. These are formed by the same member,
When processing with the same member becomes complicated, for example, two flange portions having different diameters may be divided and formed, and then joined by caulking or brazing.
【００１６】次に可変機構３について説明する。このも
のはタービンフレーム２のボス部２４の外周側に設けら
れ、排気流量を調節するために可変翼１を回動させるも
のであり、一例として図１に示すように、アッセンブリ
内において実質的に可変翼１の回動を生起する回動部材
３１と、この回動を可変翼１に伝える伝達部材３２とを
具えて成るものである。回動部材３１は、図示するよう
に中央部分が開口された略円板状に形成され、その周縁
部分に可変翼１と同数の伝達部材３２を等間隔で設ける
ものである。なおこの伝達部材３２は、回動部材３１に
回転自在に取り付けられる駆動要素３２Ａと、可変翼１
の基準面１５に固定状態に取り付けられる受動要素３２
Ｂとを具えて成るものであり、これら駆動要素３２Ａと
受動要素３２Ｂとが接続された状態で、回動が伝達され
る。具体的には四角片状の駆動要素３２Ａを、回動部材
３１に対して回転自在にピン止めするとともに、この駆
動要素３２Ａを受け入れ得るように略Ｕ字状に形成した
受動要素３２Ｂを、可変翼１の先端の基準面１５に固定
し、四角片状の駆動要素３２ＡをＵ字状の受動要素３２
Ｂに嵌め込み、双方を係合させるように、回動部材３１
をボス部２４に取り付けるものである。Next, the variable mechanism 3 will be described. This is provided on the outer peripheral side of the boss portion 24 of the turbine frame 2 and rotates the variable blade 1 to adjust the exhaust flow rate. As an example, as shown in FIG. The variable wing 1 includes a rotating member 31 that causes the rotation of the variable wing 1 and a transmission member 32 that transmits the rotation to the variable wing 1. The rotating member 31 is formed in a substantially disk shape with a central portion opened as shown in the figure, and the same number of transmitting members 32 as the variable wings 1 are provided at equal intervals on the peripheral edge portion. The transmission member 32 includes a driving element 32A rotatably attached to the rotating member 31, and a variable wing 1
Element 32 fixedly mounted on the reference surface 15 of the
B, and the rotation is transmitted in a state where the driving element 32A and the passive element 32B are connected. Specifically, the square-shaped driving element 32A is rotatably pinned to the rotating member 31, and the substantially U-shaped passive element 32B that can receive the driving element 32A is changed. The wing 1 is fixed to the reference surface 15 at the tip, and the square-shaped drive element 32A is connected to the U-shaped passive element 32.
B, and the rotating member 31
Is attached to the boss 24.
【００１７】なお複数の可変翼１を取り付けた初期状態
において、これらを周状に整列させるにあたっては、各
可変翼１と受動要素３２Ｂとが、ほぼ一定の角度で取り
付けられる必要があり、本実施の形態においては、主に
可変翼１の基準面１５がこの作用を担っている。また回
動部材３１を単にボス部２４に嵌め込んだままでは、回
動部材３１がタービンフレーム２と僅かに離反した際、
伝達部材３２の係合が解除されてしまうことが懸念され
るため、これを防止すべく、タービンフレーム２の対向
側から回動部材３１を挟むようにリング３３等を設け、
回動部材３１のタービンフレーム２側への押圧傾向を賦
与するものである。このような構成によって、エンジン
が低速回転を行った際には、可変機構３の回動部材３１
を適宜回動させ、伝達部材３２を介して軸部１２に伝達
し、図１に示すように可変翼１を回動させ、排気ガスＧ
を適宜絞り込んで、排気流量を調節するものである。In order to arrange the plurality of variable wings 1 circumferentially in the initial state in which a plurality of variable wings 1 are attached, it is necessary that each of the variable wings 1 and the passive element 32B be attached at a substantially constant angle. In the embodiment, the reference surface 15 of the variable wing 1 mainly performs this action. Further, if the rotating member 31 is slightly fitted to the boss portion 24, when the rotating member 31 is slightly separated from the turbine frame 2,
Since there is a concern that the engagement of the transmission member 32 may be released, a ring 33 or the like is provided so as to sandwich the rotating member 31 from the opposite side of the turbine frame 2 in order to prevent this.
This imparts a tendency of the rotating member 31 to be pressed toward the turbine frame 2. With such a configuration, when the engine rotates at low speed, the rotating member 31 of the variable mechanism 3
Is appropriately rotated and transmitted to the shaft portion 12 via the transmission member 32, and the variable wing 1 is rotated as shown in FIG.
Is appropriately reduced to adjust the exhaust flow rate.
【００１８】〔２〕排気ガイドアッセンブリの製造 （１）排気ガイドアッセンブリの製造 真空溶解によって所定の組成から成る各種超合金の成分
調整・溶解を行い、鋳造用超合金（Inconel 713C等)
は、インゴット鋳塊として、これを砂型鋳造や精密鋳造
用のマスターアロイとしてアッセンブリ部品を製造す
る。一方、圧延／鍛造用超合金(Incoloy 800H 等) は、
インゴット鋳塊、場合によって連続鍛造スラブ・ブルー
ム・ビレットにして、その後、圧延／鍛造にて超合金素
材とする。その後、加工（及び熱処理) を施してアッセ
ンブリ部品とする。[2] Manufacture of an exhaust guide assembly (1) Manufacture of an exhaust guide assembly The components of various superalloys having a predetermined composition are adjusted and melted by vacuum melting to form a casting superalloy (such as Inconel 713C).
Manufactures assembly parts as ingot ingots and as master alloys for sand casting and precision casting. On the other hand, superalloys for rolling / forging (such as Incoloy 800H)
It is made into an ingot ingot, and if necessary, into a continuously forged slab, bloom and billet, and then rolled / forged into a superalloy material. Then, it is processed (and heat-treated) to make an assembly part.
【００１９】（２）高温強度 以下表１に高温強度のデータを示す(2) High-Temperature Strength Table 1 shows data of high-temperature strength.
【００２０】[0020]
【表１】 [Table 1]
【００２１】〔３〕排気ガイドアッセンブリの被膜 （１）本発明における超合金のクロム炭化物、チタン炭
化物、タングステン炭化物、バナジウム炭化物、ニオブ
炭化物またはモリブデン炭化物による表面被膜は、あら
かじめ侵炭処理、侵窒処理を行った後に行い、具体的に
は、以下の工程で行われる。イオン化侵炭、またはイオ
ン化侵窒後、超合金素材を５００℃に予熱し、クロム、
チタン、タングステン、バナジウム、ニオブまたはモリ
ブデンを含む塩浴中に浸漬後、中和処理する。 （２）高温摺動による摩耗劣化の抑制 以下表２に摩耗劣化抑制のデータを示す。[3] Coating of Exhaust Guide Assembly (1) The surface coating of chromium carbide, titanium carbide, tungsten carbide, vanadium carbide, niobium carbide or molybdenum carbide of the superalloy according to the present invention is previously subjected to carburizing treatment and nitriding treatment. Is performed, and specifically, the following steps are performed. After ionized carburization or ionization and nitriding, preheat the superalloy material to 500 ° C,
After immersion in a salt bath containing titanium, tungsten, vanadium, niobium or molybdenum, a neutralization treatment is performed. (2) Suppression of wear deterioration due to high-temperature sliding Table 2 below shows data of wear deterioration suppression.
【００２２】[0022]
【表２】 [Table 2]
【００２３】[0023]
【発明の効果】本発明によれば、最高１０００℃にも達
する熱サイクル、排気ガス雰囲気下で長時間使用される
ことにより生ずる可変翼（ＶＧＳ）コントロールユニッ
トを構成する部材の高温強度の持続性向上と高温摺動に
よる摩耗劣化の抑制を図ることができる。According to the present invention, the heat cycle of up to 1000 ° C. and the sustainability of the high-temperature strength of the members constituting the variable blade (VGS) control unit caused by prolonged use in an exhaust gas atmosphere. Improvement and suppression of wear deterioration due to high-temperature sliding can be achieved.
【図１】本発明に係るタービンフレームを組み込んだＶ
ＧＳタイプのターボチャージャを示す斜視図（ａ）、並
びに排気ガイドアッセンブリを示す分解斜視図（ｂ）で
ある。FIG. 1 shows a V incorporating a turbine frame according to the present invention.
FIG. 2A is a perspective view showing a GS type turbocharger, and FIG. 2B is an exploded perspective view showing an exhaust guide assembly.
１ 可変翼 ２ タービンフレーム ３ 可変機構 １１ 翼部 １２ 軸部 １３ テーパ部 １４ 鍔部 １５ 基準面 ２１ フレームセグメント ２２ 保持部材 ２３ フランジ部 ２３Ａ フランジ部（小） ２３Ｂ フランジ部（大） ２４ ボス部 ２５ 受入孔 ２６ カシメピン ２７ ピン孔 ３１ 回動部材 ３２ 伝達部材 ３２Ａ 駆動要素 ３２Ｂ 受動要素 ３３ リング Ａ 排気ガイドアッセンブリ ｈ 羽根高さ Ｇ 排気ガス Ｔ 排気タービン Reference Signs List 1 variable blade 2 turbine frame 3 variable mechanism 11 blade 12 shaft 13 taper 14 flange 15 reference surface 21 frame segment 22 holding member 23 flange 23A flange (small) 23B flange (large) 24 boss 25 receiving Hole 26 Caulking pin 27 Pin hole 31 Rotating member 32 Transmission member 32A Drive element 32B Passive element 33 Ring A Exhaust guide assembly h Blade height G Exhaust gas T Exhaust turbine
───────────────────────────────────────────────────── フロントページの続き (51)Int.Cl.7 識別記号 ＦＩ テーマコート゛(参考） Ｃ２３Ｃ 10/24 Ｆ０２Ｂ 37/12 ３０１Ｑ Ｆターム(参考） 3G005 EA15 EA16 FA13 FA30 FA43 FA46 GA04 GB24 GB86 JA16 JA17 JA45 KA03 KA05 3G071 AB06 BA09 BA22 BA26 DA01 FA05 GA02 HA04 JA04 4K028 AA01 AB06 BA03 BA13 CC03 CD01 ──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. 7 Identification symbol FI Theme coat ゛ (Reference) C23C 10/24 F02B 37/12 301Q F term (Reference) 3G005 EA15 EA16 FA13 FA30 FA43 FA46 GA04 GB24 GB86 JA16 JA17 JA45 KA03 KA05 3G071 AB06 BA09 BA22 BA26 DA01 FA05 GA02 HA04 JA04 4K028 AA01 AB06 BA03 BA13 CC03 CD01
Claims (2)
を適宜調節して排気タービンを回転させる可変翼と、 この可変翼を排気タービンの外周部において回動自在に
支持するタービンフレームと、 この可変翼を適宜回動させ、排気ガスの流量を調節する
可変機構とを具え、 少ない排気流量を可変翼によって絞り込み、排気の速度
を増し、低速回転時にも高出力を発揮できるようにした
ＶＧＳタイプのターボチャージャにおける排気ガイドア
ッセンブリにおいて、 前記排気ガイドアッセンブリを構成する耐熱部材が、超
合金であることを特徴とする、 超合金により構成される耐久性を向上させたＶＧＳタイ
プターボチャージャの排気ガイドアッセンブリ。A variable blade for rotating an exhaust turbine by appropriately adjusting a flow rate of exhaust gas discharged from an engine; a turbine frame rotatably supporting the variable blade on an outer peripheral portion of the exhaust turbine; The VGS type is equipped with a variable mechanism that adjusts the flow rate of exhaust gas by appropriately rotating the blades. The variable exhaust blades narrow down a small amount of exhaust gas to increase the exhaust speed and to achieve high output even at low speed rotation. An exhaust guide assembly for a VGS type turbocharger, comprising a superalloy and having improved durability, wherein a heat-resistant member constituting the exhaust guide assembly is a superalloy.
請求項１記載の耐熱部材の表面を、クロム炭化物、チタ
ン炭化物、タングステン炭化物、バナジウム炭化物、ニ
オブ炭化物またはモリブデン炭化物で被膜することを特
徴とする、 超合金により構成される耐久性を向上させたＶＧＳタイ
プターボチャージャの排気ガイドアッセンブリ。2. The surface of the heat-resistant member according to claim 1, which constitutes the exhaust guide assembly, is coated with chromium carbide, titanium carbide, tungsten carbide, vanadium carbide, niobium carbide or molybdenum carbide. VGS type turbocharger exhaust guide assembly with improved durability made of alloy.
Priority Applications (11)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2001140116A JP2002332851A (en) | 2001-05-10 | 2001-05-10 | Exhaust guide assembly for vgs turbocharger with improved durability composed of superalloy |
| KR1020107027054A KR20110003393A (en) | 2001-05-10 | 2002-05-10 | Method of producing raw material for variable vanes applicable for exhaust guide assembly for vgs type turbo charger improved in heat resistance |
| US10/476,789 US20040213665A1 (en) | 2001-05-10 | 2002-05-10 | Exhaust gas assembly with improved heat resistance for vgs turbocharger, method for manufacturing heat resisting member applicable thereto, and method for manufacturing shaped material for adjustable blade applicable thereto |
| EP02769562A EP1396620A4 (en) | 2001-05-10 | 2002-05-10 | EXHAUST GAS GUIDE ASSEMBLY FOR IMPROVED HARD RESISTANCE TYPE VGS-TYPE TURBOCHARGER, METHOD FOR PRODUCING HEAT-RESISTANT ELEMENTS USED THEREWITH, AND PROCESS FOR PRODUCING VARIABLE BLADE-BASED RAW MATERIALS USED IN SAID ASSEMBLY |
| PCT/JP2002/004552 WO2002092979A1 (en) | 2001-05-10 | 2002-05-10 | 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 |
| HK05101579.2A HK1069196B (en) | 2001-05-10 | 2002-05-10 | A method for manufacturing a heat resisting member applicable to an exhaust gas guide assembly of a gas turbocharger |
| KR10-2003-7014587A KR20040028753A (en) | 2001-05-10 | 2002-05-10 | 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 |
| CN2007101407176A CN101187316B (en) | 2001-05-10 | 2002-05-10 | Exhaust guide assembly for variable giometry shape turbocharger with improved high-temperature endurance |
| CNB028139240A CN100340749C (en) | 2001-05-10 | 2002-05-10 | Method of manufacturing heat-resistant part applicable to exhaust guide assembly of variable geometry turbocharger |
| US12/213,985 US20090145523A1 (en) | 2001-05-10 | 2008-06-26 | Method for manufacturing heat resisting member applicable to an exhaust gas guide assembly with improved heat resistance for VGS turbocharger |
| US12/980,924 US20110308084A1 (en) | 2001-05-10 | 2010-12-29 | Method for manufacturing heat resisting member applicable to an exhaust gas guide assembly with improved heat resistance for vgs turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2001140116A JP2002332851A (en) | 2001-05-10 | 2001-05-10 | Exhaust guide assembly for vgs turbocharger with improved durability composed of superalloy |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2002332851A true JP2002332851A (en) | 2002-11-22 |
Family
ID=18986775
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2001140116A Pending JP2002332851A (en) | 2001-05-10 | 2001-05-10 | Exhaust guide assembly for vgs turbocharger with improved durability composed of superalloy |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2002332851A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2013213494A (en) * | 2012-03-09 | 2013-10-17 | Ihi Corp | Variable nozzle unit and variable displacement type supercharger |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03136846A (en) * | 1989-10-23 | 1991-06-11 | Toshiba Corp | Preparation of heat-resistant and abrasion-resistant member |
| JPH084544A (en) * | 1992-09-21 | 1996-01-09 | Asea Brown Boveri Ag | Turbosupercharger for heavy oil operation |
| JP2000064849A (en) * | 1998-08-24 | 2000-02-29 | Akita Fine Blanking:Kk | Variable vane applied to variable vane type turbo- charger and manufacture thereof |
-
2001
- 2001-05-10 JP JP2001140116A patent/JP2002332851A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03136846A (en) * | 1989-10-23 | 1991-06-11 | Toshiba Corp | Preparation of heat-resistant and abrasion-resistant member |
| JPH084544A (en) * | 1992-09-21 | 1996-01-09 | Asea Brown Boveri Ag | Turbosupercharger for heavy oil operation |
| JP2000064849A (en) * | 1998-08-24 | 2000-02-29 | Akita Fine Blanking:Kk | Variable vane applied to variable vane type turbo- charger and manufacture thereof |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2013213494A (en) * | 2012-03-09 | 2013-10-17 | Ihi Corp | Variable nozzle unit and variable displacement type supercharger |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2422842C (en) | Establishing a throat area of a gas turbine nozzle, and a technique for modifying the nozzle vanes | |
| US11231046B2 (en) | Aluminum airfoil | |
| US7510779B2 (en) | Low-sulfur article having a platinum aluminide protective layer and its preparation | |
| EP1396620A1 (en) | 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 | |
| US4473336A (en) | Turbine blades | |
| JP2008095541A (en) | Turbocharger | |
| US7189459B2 (en) | Turbine blade for extreme temperature conditions | |
| EP1396621B1 (en) | Surface-reformed exhaust gas guide assembly of vgs type turbo charger, and method of surface-reforming component member thereof | |
| CN101613819A (en) | Single crystal nickel-based superalloy composition, component and manufacturing method thereof | |
| JP2002332851A (en) | Exhaust guide assembly for vgs turbocharger with improved durability composed of superalloy | |
| US10208619B2 (en) | Variable low turbine vane with aft rotation axis | |
| JP2002332553A (en) | Exhaust guide assembly of vgs type turbocharger consisting of member with rare earth element or the like added and having improved high temperature durability | |
| JP2002332860A (en) | Exhaust guide assembly for vgs turbocharger with improved durability composed of heat resisting member with increased carbon solid solubility at high temperature | |
| JP4624595B2 (en) | VGS type turbocharger exhaust guide assembly with surface modification | |
| JP2002332859A (en) | Exhaust guide assembly for vgs turbocharger with improved high-temperature durability composed of martensitic stainless steel doped with tungsten or the like | |
| JPS6013910A (en) | Exhaust valve | |
| JP2002332857A (en) | Exhaust guide assembly for vgs turbocharger applied with surface modification | |
| JP2002332855A (en) | Surface modification method for constituent member of exhaust guide assembly in vgs turbocharger and exhaust guide assembly applied with surface modification method | |
| JP2010216283A (en) | Variable blade of vgs type turbocharger | |
| JP2001049421A (en) | Titanium alloy engine valve and surface treatment method thereof | |
| JP2002332852A (en) | Exhaust guide assembly for vgs turbocharger applied with surface modification | |
| JP2002332861A (en) | Exhaust emission guide assembly of vgs turbocharger formed of highly carbonized members and having increased hot hardness | |
| CN115013078A (en) | Bimetallic Variable Geometry Turbocharger Blade and Method of Manufacturing Using Laser Cladding | |
| JP2926886B2 (en) | Composite material and method for producing the same | |
| CN114472890A (en) | Method for combined sintering and surface treatment of variable geometry turbocharger blades |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20080225 |
|
| A521 | Written amendment |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20080226 |
|
| A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20100420 |
|
| A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20100907 |