Compressor blade and production and use of a compressor blade

The invention relates to a compressor blade of a compressor which, along a main axis, comprises a blade base, a platform area and an adjacent blade profile having a profile tip. The blade profile is configured by a convex wall at the suction end and a concave wall at the pressure end opposite the wall at the suction end. These surfaces extend, with respect to a flow medium, from a leading edge to a trailing edge, a profile center line extending in the center between the two. A front face is arranged on the profile tip at an angle to the main axis, a sealing lip at least partially extending from the leading edge to the trailing edge and the blade profile including the sealing lip having a blade profile height extending in the direction of the main axis. In order to allow for an inexpensive compressor blade having improved aerodynamic properties and a modified sealing lip while having the same sealing properties, the height of the sealing lip is less than 2 percent of the height of the blade profile.

CROSS REFERENCE TO RELATED APPLICATIONS

This application is the US National Stage of International Application No. PCT/EP2005/052848, filed Jun. 20, 2005 and claims the benefit thereof. The International Application claims the benefits of European application No. 04018728.8 filed Aug. 6, 2004, both of the applications are incorporated by reference herein in their entirety.

FIELD OF INVENTION

The invention relates to a compressor blade for a compressor, which blade, along a main axis, has a blade root, a platform section and a blade profile, with a blade tip, adjoining the platform section, which blade profile is formed by a convex suction side wall and a concave pressure side wall opposite the suction side wall, which walls, with regard to a flow medium, extend from a leading edge to a trailing edge, and between which a profile center line extends in the middle, wherein an end face, which is disposed transversely to the main axis, is located on the profile tip, upon which end face a sealing lip, which is formed in one piece with the blade profile, extends along the profile center line at least partially from the leading edge to the trailing edge, at a distance from the suction side wall and from the pressure side wall, and the blade profile, including the sealing lip, has a blade profile height which extends in the direction of the main axis.

BACKGROUND OF THE INVENTION

A turbine blade, with a sealing lip which is cast on the blade airfoil, is known from U.S. Pat. No. 6,039,531. The sealing lip extends in the middle between suction side and pressure side on the profile tip.

Furthermore, a compressor rotor blade, which on its free end of the blade profile has an end face upon which a lip-like rib extends in the region of the suction side of the blade profile from a leading edge to a trailing edge, is known from JP-A-2000130102. The rib of the compressor rotor blade serves as a sealing element during operation of the compressor in order to reduce the tip clearance losses in the compressor, which losses occur between the blade tip and the boundary of the compressor duct.

The production of such a sealing rib on the suction side of the blade with a feathered edge can be cost-intensive, especially in the case of blades which are sharply corrected in the tip region, i.e. blades which are especially sharply curved in the tip region, since the production or the contour milling, as the case may be, is carried out by a five-axis miller. After milling the suction side wall and the sealing lip geometry, the blade is ground manually on the suction side in order to achieve the necessary surface finish quality. This manual machining leads to frequent manufacturing errors with corresponding disadvantages, such as scrap or non-optimum contours, as the case may be.

SUMMARY OF INVENTION

It is the object of the invention, therefore, to disclose an aerodynamically improved compressor blade without reducing the sealing action of the sealing lip. Furthermore, it is the object of the invention to disclose a cost-effective method for producing such a compressor blade, and also a use of the latter.

The object which relates to the compressor blade is achieved by means of the features of the claims, the object which relates to the production is achieved by means of the features of the claims, and the object which relates to the use is achieved by means of the features of the claims.

The invention proposes that the height of the sealing lip is less than two percent of the height of the blade profile.

The invention starts from the knowledge that a sealing lip of a compressor blade according to the invention, is produced cost-effectively by means of a three-axis milling unit, although on account of the geometrically exacting, aerodynamic shape of the blade profile of the compressor blade, this is produced by means of a five-axis milling unit or by means of close-tolerance forging.

For production, therefore, a simpler production method and/or a machine, which is more cost-effective in use, can be used for it.

This is especially of advantage in the case of compressor blades which are comparatively sharply curved in the tip region.

Moreover, error-prone and cost-intensive manufacturing steps, such as a manual reworking, can be dispensed with, without replacement. The production process is curtailed. Furthermore, the omission of the manual reworking leads to a significantly higher process reliability.

The accuracy of the geometry of the sealing lip according to the invention can be also checked and inspected more simply than that of a sealing lip which is constructed parallel to the suction side. This leads to a further reduction of the production cost.

According to the invention, the height of the sealing lip is at most two percent of the height of the blade profile. Up to now, a sealing lip which was connected in one piece to the blade profile had a greater height for production engineering reasons.

Calculations show that the newly selected size of the sealing lip on the end face has no negative influence on the aerodynamic performance of the blade profile, on the contrary, the aerodynamically optimized, effective area of the blade profile is increased on account of the lower sealing lip, which, in the case of a compressor fitted with the compressor blade according to the invention, leads to improved aerodynamics, to smaller flow disturbances in the tip region of the blade profile, and altogether to an increased efficiency.

Advantageous developments are disclosed in the dependent claims.

In particular, if the sealing lip has a side face on the suction side and a side face on the pressure side, which side faces extend parallel to the main axis, these can be produced especially simply and, therefore, cost-effectively. Furthermore, it is advisable to manufacture the two side faces so that they also extend parallel to the profile center line. Consequently, the side faces of the sealing lip are not aerodynamically formed, i.e. not inclined to the main axis, like the contour of the side walls of the blade profile. Furthermore, the sealing lip reduces the tip clearance losses across the profile tip.

In an advantageous development, the side faces of the sealing lip are interconnected by means of a feathered surface, which feathered surface is disposed perpendicularly to the radius of the rotor of the compressor. Therefore, a cylindrical gap can be formed between casing or hub component parts, as the case may be, and the compressor blade, which reduces the clearance losses.

The compressor blade according to the invention can be advantageously used in the same way as a rotor blade as also a stator blade.

Especially preferred is the development in which at least one side face of the sealing lip is interconnected to the end face by a transition radius, the size of which is at most 25 percent of the height of the sealing lip. On account of the especially small transition radius, an exceptionally low sealing lip height can be achieved. The production of such a transition radius is carried out cost-effectively together with the sealing lip by means of a shank end milling cutter on a three-axis milling unit. However, hitherto sharply curved blade profiles with a sealing lip which was milled with a large transition radius, had a greater sealing lip height, especially in the center region between leading edge and trailing edge, than in the region of the leading edge and trailing edge, which up to now led to flow disturbances. This convex shape of the sealing lip or its height, as the case may be, can be avoided by significantly smaller transition radii.

DETAILED DESCRIPTION OF INVENTION

Compressors and gas turbines, and also their operating modes, are generally known. For this purpose,FIG. 1shows a gas turbine1with a rotor5which is rotatably mounted around a rotational axis3.

The gas turbine1has an intake duct7, a compressor9, a toroidal annular combustion chamber11and a turbine unit13along the rotational axis3.

Stator blades15and rotor blades17are arranged in rings in each case both in the compressor9and in the turbine unit13. In the compressor9in this case a stator blade ring21follows a rotor blade ring19. The rotor blades17in this case are fastened on the rotor5by means of rotor discs23, whereas the stator blades15are mounted on the casing25in a fixed manner.

Rings21of stator blades15are also arranged in the turbine unit13, which stator blade rings are followed by a ring of rotor blades17in each case, viewed in the direction of the flow medium.

The respective blade profiles of the stator blades15and the rotor blades17in this case extend radially in an annular flow passage27.

During operation of the gas turbine1, air29from the compressor9is inducted through the intake duct7and compressed. At the outlet31of the compressor9, the compressed air is guided to the burners33which are provided on a ring which lies on the annular combustion chamber11.

In the burners, the compressed air29is mixed with a fuel35, which mixture is combusted in the annular combustion chamber11, forming a hot gas37. The hot gas37then flows through the flow passage27of the turbine unit13past stator blades15and rotor blades17. In doing so, the hot gas37is expanded on the rotor blades17of the turbine unit13with work output effect. As a result of this, the rotor5of the gas turbine1is set in a rotational movement which serves for drive of the compressor9and for drive of a driven machine, which is not shown.

FIG. 2shows a compressor blade50in a perspective view. The compressor blade50has a blade root55, a platform section57with a platform59, and a blade profile61along a main axis53. During operation of the compressor9, the blade profile61is flow-washed by air29which flows onto the blade profile61at a leading edge63and flows off from a trailing edge65. The blade profile61is formed by a pressure side wall67and by a suction side wall69, and has a blade height H which extends in the direction of the main axis53.

A profile center line71extends from the leading edge63to the trailing edge65, which profile center line at each point of its progression has a perpendicular, which perpendicular74intersects both the suction side wall69and the pressure side wall67. In this case, a first distance A between the intersection points of the perpendiculars74with the profile center line71and the pressure side wall67with the perpendiculars74in each case, is identical to a second distance B which exists between the intersection points of the profile center line71with the perpendiculars74and the suction side wall69with the perpendiculars74.

In addition, the blade profile61, on its profile tip72which faces away from the platform59, has an end face73upon which a sealing lip75is located. The sealing lip75is narrower than the blade profile61, extends from leading edge63to trailing edge65, and extends along the profile center line71, consequently in the space between the contour of the suction side wall69and the pressure side wall67.

The sealing lip75, also referred to as a feathered edge, has a first side surface77which faces the pressure side wall67, and a second side face79which faces the suction side wall69.

The curved side faces77,79of the sealing lip75extend parallel to the main axis53and also parallel to the profile center line71, whereas the suction side wall69of the blade profile61and also the pressure side wall67of the blade profile61extend in an inclined manner for aerodynamic reasons, i.e. extend at an angle to the main axis53. Compared with a blade of the prior art, a simplified production of the sealing lip75can be achieved by this.

Moreover, the side faces77,79of the sealing lip75are interconnected by means of a feathered surface81, which feathered surface81is disposed perpendicularly to the radius of the rotor5of the compressor9.

The sealing lip75has a height HL which is oriented parallel to the main axis53, which height is measured between the end face73of the blade profile and the feathered surface81and is part of the blade profile height H.

FIG. 3shows a detailed view of a feathered edge according to the invention. In this case, it is clearly apparent that the sealing lip75extends centrally between the suction side wall69and the pressure side wall67, from the leading edge63to the trailing edge65, with side faces77,79which are oriented parallel to the main axis53and to the profile center line71.

The side faces77,79merge into the end face73via a transition radius R which is advantageously at most 25 percent of the sealing lip height HL. As a result of this, an especially low sealing lip can be produced, the height HL of which is at most 2 percent of the blade airfoil height H.

By means of the new geometry and position of the sealing lip75, error-prone and cost-intensive manufacturing steps are dispensed with. As a result of this, both the manufacturing costs and the scrap rate of the produced compressor blades50can be reduced. A worsening of the tip clearance losses through the radial gap between compressor blade50and inner casing does not occur in this case, just as little as flow losses on account of the insignificantly reduced, maximum possible aerodynamically effective profile face: