Rotary kinetic fluid motors or pumps – Working fluid passage or distributing means associated with... – Vane or deflector
Reexamination Certificate
2001-11-30
2003-12-02
Look, Edward K. (Department: 3745)
Rotary kinetic fluid motors or pumps
Working fluid passage or distributing means associated with...
Vane or deflector
Reexamination Certificate
active
06655912
ABSTRACT:
CROSS-REFERENCE TO RELATED APPLICATIONS
This application claims priority to European Application No. 00 870 290.4, filed Dec. 6, 2000, the disclosure of which is herein incorporated by reference in its entirety.
BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention relates to a guide vane stage of a compressor, comprising a succession of guide vane or stator stages separated by rotor stages of rotating vanes, each guide vane stage consisting of fixed vanes connecting an inner ring to an outer ring.
2. Description of the Related Art
Coaxial compressors are well known per se, and are used in several types of application. In particular, they are used in twin-structure engines, turbofan engines and turbojet engines. It is also noted that they are present in power stations. These low-pressure or high-pressure compressors substantially consist of several rotating vane stages or rotor stages separated by stator stages or guide vane stages whose function is to reposition (rectify) the speed vector of the fluid exiting the preceding stage before sending it to the next compartment.
Each of these guide vane stages substantially consists of fixed vanes connecting an outer ring to an inner ring, both of which are concentric.
The problem is that these guide vane stages are submitted to relatively large forces due, in particular, to the vibrations, which rapidly cause wear by fatigue.
In order to solve this problem of fatigue, it has been proposed to rigidify the rings. By rigidifying the rings, and in particular the inner rings of the first compression stages, it is in fact possible to shift the Eigen frequencies of certain stress modes which excessively wear said rings.
Several rigidification solutions have been envisaged. In particular, the use of stiffeners in the form of strips which are machined on the inner ring or on the outer ring and on the non-functional side has been proposed. It has also been proposed to machine steps into the metal sheet of the inner or outer ring. These strips or steps may also consist of a component mounted by welding or riveting. In addition, in order to improve the sealing from one stage to the next, it is common practice to arrange under the metal sheet of the inner ring of the guide vane an elastomeric member which seals the fixed vane to the inner ring and which will also act as a seal between the rotating and fixed members. This makes it possible to avoid any backflow of gases towards the preceding stage, which might lead to an engine stall in the case of a turbofan engine.
Nevertheless, the various solutions proposed according to the prior art are relatively expensive solutions given that a relatively large amount of material is needed to machine the sheet metal of the rings.
Another major problem in the case of the guide vane stages of a compressor is that said vanes should be securely fastened to the rings in a particularly efficient manner. Specifically, this fastening of the vanes to the rings must be optimal so as to be able to withstand accidents such as the breaking of a vane or the ingestion of a foreign body such as a bird into said turbojet engine.
Furthermore, a displacement of the vanes relative to the rings causes extensive wear with a “fatigue crack” which can lead to the breaking of said vanes or even of the ring.
Usually, the vanes are fastened to the rings, both the inner and outer ring, by means of rivets or welds. Nevertheless, the use of these means of fastening has the major drawback of disrupting the flow and of generating a loss of pressure in the aerodynamic stream.
British Patent No. A-748 912 discloses a blade assembly for compressors comprising a plurality of blade elements and a shroud structure, said shroud structure consisting of an inner skin and an outer skin, said skins being formed with slots in radially-aligned pairs. The end of each blade element is mounted in the shroud structure by extending through an aligned pair of said slots and is retained in position by means of a first mechanical abutment between said end and one of said skins to limit the length of the blade element which extends through the slots, and by means of a second mechanical abutment to prevent disengagement of the blade element from the slots. The first mechanical abutment consists in a shoulder provided on said end which co-operate in abutment with the inner surface of the outer skin. The second mechanical abutment consists in an associated strip-like wedging member co-operating with a dovetail notch provided on said ends and with the outer surface of the outer skin.
U.S. Pat. No. 2,812,159 discloses a device for assembling vanes comprising a series of U-shaped components, each of said vanes being provided with a hole at the bottom of the “U” which fits the free end of said vanes, said assembling being secured by means of fastening means comprising among other things screws and which are adapted so as to prevent lateral and axial movements of the vanes. However, the problem of the disruption of the aerodynamic flow stream encountered when screws or similar fastening means are used, is still existing.
French Patent No. A-2 671 140 discloses a stator assembly in a turbocompressor, comprising an outer ring and a series of stator vanes retained to said outer ring, wherein the outer end of each vane takes the form of a wedge and the outer ring has prismatic slots complementary to said wedge so that the outer ring fits said prismatic slots and the stator vanes are retained thereby to said outer ring. The stator vanes are maintained in position by means of both notches and a metallic element, preferably elastic, which rests on the end face of each vane.
U.S. Pat. No. 5,569,019 discloses a fan stator assembly comprising an inner and outer shrouds provided with apertures through which vanes pass, said vanes being radially restrained to the inner and outer shrouds by means of seals. Each vane substantially consists of two parts, an airfoil section and a foot. The vanes preferably comprise a non-metallic composite material consisting of a plurality of compression molded, heat cured plies, including plies of para-aramid fibers which are continuous throughout the airfoil section and the foot of the vanes but are discontinuous (cut) at the junction of airfoil section with foot.
SUMMARY OF THE INVENTION
The present invention aims to propose a solution for combining the functions of rigidification of the inner ring and retention of the vanes of a guide vane stage of an axial compressor.
In particular, the present invention aims to provide a solution which offers great ease of assembly and which requires no additional assembly operations.
The present invention aims also to propose a solution in which the aerodynamic flow stream is not affected by the presence of welds or rivets on the ring.
The present invention aims also to produce a solution of rather low cost.
The present invention relates to a guide vane stage of a compressor comprising two rings, an inner ring and an outer ring, which are both concentric and preferably circular and connected to each other via a series of fixed vanes. At least the inner ring is provided with holes or apertures that allow said vanes to pass through these holes. The vanes themselves have, at their end that will be arranged on the inner ring side, a second aperture intended to allow the passage of a retaining and rigidifying component having an elastic function. This retaining and rigidifying component will advantageously make it possible to securely fasten the vanes in pairs on the non-functional side, that is to say on the inner face side, of the inner ring.
According to one particularly preferred embodiment, this retaining and rigidifying component is in the form of a metal sheet cut, shaped and folded in two and is provided with two flat stubs intended to be housed in the apertures of two successive vanes.
In a particularly advantageous manner, the fact that this component is folded allows it to act as a spring, for example a spring of “hairpin” type.
In a particularly advantageous manner, it is observ
Edgar Richard A.
Knobbe Martens Olson & Bear LLP
Look Edward K.
Techspace Aero S.A.
LandOfFree
Guide vane stage of a compressor does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Guide vane stage of a compressor, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Guide vane stage of a compressor will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-3162978