JPH08219092A - Clearance forming coating for compressor - Google Patents
Clearance forming coating for compressorInfo
- Publication number
- JPH08219092A JPH08219092A JP2271095A JP2271095A JPH08219092A JP H08219092 A JPH08219092 A JP H08219092A JP 2271095 A JP2271095 A JP 2271095A JP 2271095 A JP2271095 A JP 2271095A JP H08219092 A JPH08219092 A JP H08219092A
- Authority
- JP
- Japan
- Prior art keywords
- impeller blade
- compressor
- casing shroud
- tip
- clearance
- 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
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、ガスタービンエンジン
等に適用される圧縮機の造隙コーティングに関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gap coating for a compressor applied to a gas turbine engine or the like.
【０００２】[0002]
【従来の技術】従来の遠心圧縮機は、図３に示すように
オープンタイプインペラ１、ケーシングシュラウド２及
びディフューザ４から構成され、インペラブレード１Ａ
先端部とそれに相対するケーシングシュラウド２内面部
の間に運転中双方の接触しないように隙間１Ｂ’が設け
られていた。2. Description of the Related Art A conventional centrifugal compressor comprises an open type impeller 1, a casing shroud 2 and a diffuser 4, as shown in FIG.
A gap 1B ′ was provided between the tip end portion and the inner surface portion of the casing shroud 2 opposite to the tip end portion so as not to come into contact with each other during operation.
【０００３】[0003]
【発明が解決しようとする課題】一般に、オープンタイ
プインペラを有する遠心圧縮機では、図３におけるイン
ペラブレード１Ａ先端部の隙間１Ｂ’を小さくするほど
隙間部からの気体のリークＢが少なくなり、空力性能は
向上するが、反面、インペラブレード１Ａ先端部が運転
中に接触し、インペラブレード１Ａ及びケーシングシュ
ラウド２の双方が損傷する可能性がある。Generally, in a centrifugal compressor having an open type impeller, the smaller the clearance 1B 'at the tip of the impeller blade 1A in FIG. 3, the less the gas leak B from the clearance and the aerodynamics. Although the performance is improved, on the other hand, there is a possibility that both the impeller blade 1A and the casing shroud 2 will be damaged due to the contact of the tip of the impeller blade 1A during operation.
【０００４】従来の遠心圧縮機においては、この損傷を
避けるべく、インペラブレード１Ａ先端部の隙間１Ｂ’
を大きく設定しているため、空力性能を向上させること
ができないという課題があった。本発明は上記の課題を
解決しようとするもである。In the conventional centrifugal compressor, in order to avoid this damage, the gap 1B 'at the tip of the impeller blade 1A.
However, there is a problem that the aerodynamic performance cannot be improved because of the large setting. The present invention is intended to solve the above problems.
【０００５】[0005]
【課題を解決するための手段】本発明の圧縮機の造隙コ
ーティングは、インペラブレードを有するオープンタイ
プインペラと、ケーシングシュラウドを備えた圧縮機に
おいて、ケーシングシュラウドに対向するインペラブレ
ードの先端に設けられ耐摩耗性を有する溶射材からなる
第１の溶射部、および同第１の溶射部に対向する上記ケ
ーシングシュラウドの内面に設けられ被削性を有する溶
射材からなる第２の溶射部により形成されたことを特徴
としている。The compressor gap coating of the present invention is provided on the tip of the impeller blade facing the casing shroud in an open type impeller having an impeller blade and a compressor having a casing shroud. It is formed by a first sprayed part made of a sprayed material having wear resistance, and a second sprayed part made of a sprayable material having machinability provided on the inner surface of the casing shroud facing the first sprayed part. It is characterized by that.
【０００６】[0006]
【作用】上記において、インペラブレードの先端とこれ
に対向するケーシングシュラウドの内面には、それぞれ
第１と第２の溶射部が設けられているため、その間隙は
従来の装置の場合と比べて狭くなったため、圧縮機の空
力性能の向上が可能となる。In the above description, since the first and second sprayed portions are provided on the tip of the impeller blade and the inner surface of the casing shroud which faces the tip of the impeller blade, the gap is narrower than in the case of the conventional apparatus. As a result, the aerodynamic performance of the compressor can be improved.
【０００７】また、第１の溶射部は耐摩耗性を有する溶
射材がインペラブレードの先端に溶射されて形成され、
第２の溶射部は被削性を有する溶射材がケーシングシュ
ラウドの内面に溶射されて形成されているため、インペ
ラブレードの先端がケーシングシュラウドに接触した場
合は、第１の溶射部が第２の溶射部を削り取るだけで、
それぞれの母材に損傷を与えることがない。The first sprayed portion is formed by spraying a wear-resistant sprayed material onto the tip of the impeller blade.
The second sprayed portion is formed by spraying a sprayable material having machinability on the inner surface of the casing shroud. Therefore, when the tip of the impeller blade contacts the casing shroud, the first sprayed portion is Just scraping off the sprayed part,
Does not damage each base material.
【０００８】[0008]
【実施例】本発明の一実施例に係るガスタービンエンジ
ンの遠心圧縮機について、図１により説明する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A centrifugal compressor for a gas turbine engine according to an embodiment of the present invention will be described with reference to FIG.
【０００９】図１に示す本実施例は、インペラブレード
１Ａが設けられたオープンタイプインペラ１と、ケーシ
ングシュラウド２と、ディフューザ４を備えた遠心圧縮
機において、インペラブレード１Ａの先端にＣｒ−Ｍｏ
−Ｓｉ−Ｃ−Ｃｕ−Ｆｅの溶射により形成された溶射部
３Ａと、ケーシングシュラウド２の内面にＮｉ−Ａｌの
溶射により形成された溶射部３Ｂを備えている。The present embodiment shown in FIG. 1 is a centrifugal compressor having an open type impeller 1 provided with an impeller blade 1A, a casing shroud 2 and a diffuser 4, and a Cr-Mo at the tip of the impeller blade 1A.
A sprayed portion 3A formed by spraying —Si—C—Cu—Fe and a sprayed portion 3B formed by spraying Ni—Al on the inner surface of the casing shroud 2 are provided.
【００１０】上記において、インペラブレード１Ａの先
端とケーシングシュラウド２の内面にそれぞれ形成され
た溶射部３Ａ，３Ｂは、いずれもダイヤモンド・ジェッ
ト溶射プロセスにより形成されたものであり、それぞれ
に溶射部３Ａ，３Ｂが形成されたことにより、その間隙
１Ｂは従来の装置における間隙１Ｂ’の約２／３〜１／
２となった。In the above description, the sprayed portions 3A and 3B formed on the tip of the impeller blade 1A and the inner surface of the casing shroud 2 are both formed by the diamond jet spraying process, and the sprayed portions 3A and 3A are respectively formed. Since the gap 3B is formed, the gap 1B is about 2/3 to 1 / the gap 1B 'in the conventional device.
It became 2.
【００１１】そのため、吸入空気ＡのリークＢは減少
し、空力性能を大幅に向上させることができ、図２に示
すように流量で約１．５％、効率で約１％向上させるこ
とができた。Therefore, the leak B of the intake air A is reduced, and the aerodynamic performance can be greatly improved. As shown in FIG. 2, the flow rate can be improved by about 1.5% and the efficiency can be improved by about 1%. It was
【００１２】また、インペラブレード１Ａの溶射部３Ａ
は、Ｃｒ−Ｍｏ−Ｓｉ−Ｃ−Ｃｕ−Ｆｅにより形成され
ているため、耐摩耗性に優れ、また、ケーシングシュラ
ウド２の溶射部３Ｂは、Ｎｉ−Ａｌにより形成されてい
るため、被削性に優れている。Further, the sprayed portion 3A of the impeller blade 1A
Is excellent in wear resistance because it is formed of Cr-Mo-Si-C-Cu-Fe, and because the sprayed portion 3B of the casing shroud 2 is formed of Ni-Al, it has machinability. Is excellent.
【００１３】そのため、インペラブレード１Ａの先端が
ケーシングシュラウド２の内面に接触した場合には、ケ
ーシングシュラウド２の溶射部３Ｂがインペラブレード
１Ａの溶射部３Ａにより削り取られるだけで、それぞれ
の母材に損傷を与えることがなくなった。Therefore, when the tip of the impeller blade 1A comes into contact with the inner surface of the casing shroud 2, the sprayed portion 3B of the casing shroud 2 is only scraped off by the sprayed portion 3A of the impeller blade 1A, and the respective base materials are damaged. No longer give.
【００１４】なお、本実施例は、ガスタービン用遠心圧
縮機への適用例を示したが、これに限定されるものでは
なく、少なくともオープンタイプインペラを有する圧縮
機を含んで構成される回転機械であれば、何れにも適用
可能である。Although the present embodiment shows an example of application to a centrifugal compressor for a gas turbine, the present invention is not limited to this, and is a rotary machine including at least a compressor having an open type impeller. If so, it is applicable to both.
【００１５】[0015]
【発明の効果】本発明の圧縮機の造隙コーティングは、
オープンタイプインペラのインペラブレードの先端に設
けられ耐摩耗性を有する第１の溶射部と、ケーシングシ
ュラウドの内面に設けられ被削性を有する第２の溶射材
とにより形成されたことによって、インペラブレード先
端がケーシングシュラウド内面に接触した場合にも母材
に損傷を与えることがなく、その間隙を縮小させること
ができるため、間隙からの気体のリークを低減すること
ができ、圧縮機の空力性能の大幅向上が可能となる。The compressor gap coating of the present invention comprises:
The impeller blade is formed by the first thermal spraying portion having wear resistance provided at the tip of the impeller blade of the open type impeller and the second thermal spraying material having machinability provided on the inner surface of the casing shroud. Even when the tip comes into contact with the inner surface of the casing shroud, the base material is not damaged and the gap can be reduced, so that gas leakage from the gap can be reduced and the aerodynamic performance of the compressor can be reduced. Significant improvement is possible.
【図１】本発明の一実施例に係る遠心圧縮機の説明図で
ある。FIG. 1 is an explanatory diagram of a centrifugal compressor according to an embodiment of the present invention.
【図２】上記一実施例に係る遠心圧縮機の空力性能につ
いての従来のものとの比較図である。FIG. 2 is a comparison diagram of the aerodynamic performance of the centrifugal compressor according to the above embodiment with a conventional one.
【図３】従来の圧縮機の説明図である。FIG. 3 is an explanatory diagram of a conventional compressor.
１ オープンタイプインペラ １Ａ インペラブレード １Ｂ 間隙 ２ ケーシングシュラウド ３Ａ，３Ｂ 溶射部 ４ ディフューザ 1 Open type impeller 1A Impeller blade 1B Gap 2 Casing shroud 3A, 3B Spraying part 4 Diffuser
Claims (1)
プインペラと、ケーシングシュラウドを備えた圧縮機に
おいて、ケーシングシュラウドに対向するインペラブレ
ードの先端に設けられ耐摩耗性を有する溶射材からなる
第１の溶射部、および同第１の溶射部に対向する上記ケ
ーシングシュラウドの内面に設けられ被削性を有する溶
射材からなる第２の溶射部により形成されたことを特徴
とする圧縮機の造隙コーティング。1. A compressor provided with an open-type impeller having an impeller blade and a casing shroud, wherein a first thermal spray portion is provided at a tip of the impeller blade facing the casing shroud and is made of a thermal spray material having abrasion resistance, And a space spray coating for a compressor, which is formed by a second sprayed portion formed of a sprayable material having machinability provided on the inner surface of the casing shroud facing the first sprayed portion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2271095A JP3294038B2 (en) | 1995-02-10 | 1995-02-10 | Compressor gap coating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2271095A JP3294038B2 (en) | 1995-02-10 | 1995-02-10 | Compressor gap coating |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH08219092A true JPH08219092A (en) | 1996-08-27 |
| JP3294038B2 JP3294038B2 (en) | 2002-06-17 |
Family
ID=12090398
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2271095A Expired - Fee Related JP3294038B2 (en) | 1995-02-10 | 1995-02-10 | Compressor gap coating |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3294038B2 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2947016A1 (en) * | 2009-06-17 | 2010-12-24 | Snecma | Centrifugal compressor i.e. axial centrifugal compressor, for turboshaft engine i.e. turbojet engine, has abradable layer placed on casing and limiting circulation of flow of air between casing and rotor, where layer includes abradables |
| KR20150011237A (en) * | 2013-07-22 | 2015-01-30 | 삼성테크윈 주식회사 | Impeller assembly of fluid rotary machine and manufacturing method thereof |
| CN112211832A (en) * | 2019-07-09 | 2021-01-12 | 斗山英维高株式会社 | Fan assembly |
-
1995
- 1995-02-10 JP JP2271095A patent/JP3294038B2/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2947016A1 (en) * | 2009-06-17 | 2010-12-24 | Snecma | Centrifugal compressor i.e. axial centrifugal compressor, for turboshaft engine i.e. turbojet engine, has abradable layer placed on casing and limiting circulation of flow of air between casing and rotor, where layer includes abradables |
| KR20150011237A (en) * | 2013-07-22 | 2015-01-30 | 삼성테크윈 주식회사 | Impeller assembly of fluid rotary machine and manufacturing method thereof |
| CN112211832A (en) * | 2019-07-09 | 2021-01-12 | 斗山英维高株式会社 | Fan assembly |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3294038B2 (en) | 2002-06-17 |
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