专利汇可以提供ENGINE SHAFT FOR A GAS-TURBINE ENGINE专利检索,专利查询,专利分析的服务。并且A low-pressure turbine shaft (11) for a gas-turbine engine includes a fiber-composite plastic tube (13) with fiber layers provided in an inner wall area for taking up and transmitting torsional forces, and, in an outer wall area, with fiber layers suitably oriented for influencing stiffness and damping characteristics. The fiber layers are embedded in a high temperature resistant plastic matrix. A load input element (14) is an attachment flange (24) made of fiber-composite plastic material integrally formed on a fiber-composite plastic tube (13). A load output element (15) is a metallic driven protrusion inseparably connected to the fiber layers transmitting the torsional forces. Alternatively, the load input element may be provided as a metallic driving protrusion, which is firmly connected to the fiber layers taking up the torsional forces.,下面是ENGINE SHAFT FOR A GAS-TURBINE ENGINE专利的具体信息内容。
What is claimed is:
This application claims priority to German Patent Application DE 102008056018.9 filed Nov. 5, 2008, the entirety of which is incorporated by reference herein.
This invention relates to an engine shaft, in particular a low-pressure turbine shaft or a radial shaft for a gas-turbine engine, which is designed as a hollow body and provided with a load input element on a driving side and a load output element on a driven side.
A known multi-spool bypass gas-turbine engine has, arranged in the following sequence in the direction of flow, for example an air inlet, a fan, an intermediate-pressure compressor and a high-pressure compressor, a combustion chamber, a high-pressure turbine, an intermediate-pressure turbine and a low-pressure turbine. The high-pressure turbine, the intermediate-pressure turbine and the low-pressure turbine are connected to the high-pressure compressor, the intermediate-pressure compressor and the fan via concentrically arranged drive shafts, i.e. a high-pressure turbine shaft, an intermediate-pressure turbine shaft and a low-pressure turbine shaft. The fan produces a first airflow, or bypass flow, which provides propulsive thrust and a second airflow which is initially compressed in the intermediate-pressure compressor and then further compressed in the high-pressure compressor. The high-pressure turbine, the intermediate-pressure turbine and the low-pressure turbine are driven by the expanding gases released from the combustion chamber, with the gases discharged from the engine via a nozzle providing for additional propulsive thrust.
The low-pressure turbine shaft (low-pressure shaft), which is arranged concentrically to the hollow intermediate-pressure turbine shaft—or to the high-pressure turbine shaft on a two-spool gas-turbine engine—and is provided at its ends with rigidly attached coupling elements (load input element, load output element) for connection to the fan and the low-pressure turbine and transmission of high loads, has smaller diameter, greater length, lower speed and higher loading than the other two shafts. Accordingly, the low-pressure turbine shaft is a highly loaded, critical engine component which, on the one hand, shall not fail under any circumstances and, on the other hand, shall have smallest possible outer diameter to permit the use of turbine disks with smallest possible inner diameter to provide lightweight and powerful turbines. The low-pressure turbine shaft, which is usually made of steel or a nickel-base material and is forged and hollowed out, is expensive to manufacture and also heavy. In enhancing aircraft engines, an inward increase of the wall thickness of the low-pressure turbine shaft is the only way to enable the latter to transmit higher torques and attain greater length, higher speed and high stiffness with limited, smallest possible outer diameter. However, this will cause the natural frequency of the low-pressure shaft to fall and approach the natural frequency of the engine, with the consequence that, besides a higher weight of the low-pressure shaft, an increase in vibration is likely, incurring the hazard of damage or destruction of the low-pressure turbine shaft.
The requirements on the low-pressure turbine shaft apply similarly to the radial shaft connecting an external and internal gear drive, with the radial shaft being driven at both ends, although always in the same direction. As a consequence, different torques are applied to the radial shaft. Like the low-pressure shaft, the radial shaft must be designed as slender as possible.
In a broad aspect, the present invention provides for a design of the low-pressure turbine shaft or the radial shaft for a gas-turbine engine which enables high torques to be reliably transmitted while featuring reduced weight and limited outer diameter.
The present invention, in its essence, provides for a design of the respective engine shaft in the form of a fiber-composite plastic tube made of different fiber layers which—preferably in the case of the low-pressure turbine shaft—is provided, for load input, with an attachment flange in fiber-composite plastic material integrally formed on via a flaring tube section or a metallic driving protrusion inseparably incorporated in the fiber-composite structure and, for load output, with a metallic driven protrusion located at the other shaft end and inseparably incorporated in the fiber-composite structure. Furthermore, an essential concept of the present invention is to provide for a particular orientation of the fibers in the several fiber layers, actually such that the fiber layers starting out from the inner wall of the fiber-composite plastic tube are disposed at an angle suitable for taking up and transmitting torsional forces, while the fiber layers provided in the outer wall area are disposed at an angle providing for the stiffness of the fiber-composite tube. While the outer fiber layers, with an angle ranging between +/−12° and +/−5°, largely extend in the direction of the shaft axis, the fiber layers adjoining towards the inner wall, with an angle between +/−45° and +/−35°, are significantly more transversely oriented to the longitudinal axis. Orienting the fibers in the respective radius area allows the low-pressure turbine shaft to be variably designed and adapted to the respective engine performance with regard to stiffness, natural frequency and damping as well as with regard to the torsional forces to be transmitted. Integral incorporation of the metallic driving and driven protrusions into the torsional force-transmitting inner fiber layers provides for safe output of load. Manufacturing costs and weight of the low-pressure turbine shaft or the radial shaft, respectively, are low compared with metallic designs. In accordance with the loading of the low-pressure turbine shaft, a property profile of the low-pressure turbine shaft is generated in dependence of the orientation of the fiber layers which is decoupled with regard to transmittability of torsional forces and stiffness. In order to account for the different torques acting upon the radial shaft, the +/−45° fibers and the +/−35° fibers are simultaneously applied to form a fiber braid.
According to a preferred embodiment, the fiber-composite plastic tube includes a first, inner, carbon fiber layer and a second carbon fiber layer, adjoining the first layer, each arranged at an angle of +45° and −45°, a third and a fourth carbon fiber layer, each arranged at an angle of +35° and −35° as well as fifth and sixth—outer—carbon fiber layers, each arranged at an angle of +5° or −5° respectively.
In a further development of the present invention, a hose-type braid of fibers oriented at an angle of +45° and −45° is provided on the outer surface of the fiber-composite plastic tube. Preferably, the outermost fiber layer, which is provided for mechanical surface protection, is made of glass fibers.
According to a further feature of the present invention, the fiber layers are embedded in a high-temperature resistant plastic matrix preferably made of cyanate and/or phenolic resin and/or polyimides and/or polyetherether-ketones, in accordance with the temperature of the turbine shaft encountered in service.
The present invention is more fully described in light of the accompanying drawings showing a preferred embodiment. In the drawings,
The gas-turbine engine shown in
The highly-stressed low-pressure turbine shaft 11, which is supported at two points in bearing arrangements and, in the present example, has a maximum outer diameter of 100 mm and a length of 2 m, includes a fiber-composite plastic tube 13 which is provided at its one end with a load input element 14 connected to a rotor disk of the low-pressure turbine 8 and at its other end with a load output element 15 connected to the fan 2. The fiber-composite plastic tube 13 with the associated load input and load output elements 14, 15 is designed such that the low-pressure turbine shaft 11 features high natural frequency and stiffness as well as vibration-damping properties while being capable of taking up and transmitting high torsional forces and also being resistant to temperatures of up to approx. 400° C. existing in this engine area.
As can be seen in
According to the graph in
According to the part-sectional representation of the low-pressure turbine shaft 11 in
The present invention is not limited to the embodiment exemplified in the above. Also falling within the scope of the present invention is, for example, a load input element in the form of a metallic driving protrusion firmly connected to the fiber layers taking up the torsional forces.
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