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Blade and gas turbine

a gas turbine and blade technology, applied in the field of blades, to achieve the effect of reducing weight, reducing weight, and influencing the strength properties of segments

Inactive Publication Date: 2009-10-08
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0008]This connection allows particularly simple fitting of the blade trailing edge and / or the blade leading edge, since the edge segments are formed such that they can be displaced transversely with respect to the blade edge. Therefore, with the blade according to the invention, the edge segment can be exchanged without having to dismantle the blade, which shortens the repair time. Furthermore, the modular structure allows the blade edges of the main blade part, which are subject to higher stresses and are accordingly more vulnerable, to be selectively exchanged. This increases the service life of the base body segment, which is subject to less wear. Furthermore, the exchangeable regions can be deliberately matched to the mechanical and thermal demands, which leads to cost savings.
[0015]It is expedient for the blade to be designed as a guide vane or as a rotor blade. It is particularly advantageous for a blade of this type to be used in a gas turbine.

Problems solved by technology

Furthermore, the modular structure allows the blade edges of the main blade part, which are subject to higher stresses and are accordingly more vulnerable, to be selectively exchanged.

Method used

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  • Blade and gas turbine
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Examples

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Embodiment Construction

[0022]Turbomachines use blade stages, which comprise adjacent rotor blades and guide vanes, to convert flow energy into rotary energy and vice versa. The guide vanes are arranged on the machine housing, while the rotor blades are directly connected to the rotor.

[0023]A blade 1 according to the invention with a segmented trailing edge is illustrated in FIGS. 1 to 3. The blade 1 itself has a platform 2a and a main blade part 3 with a blade leading edge 4 and a blade trailing edge 5. A second platform 2b, which is formed integrally at the upper end 5a of the main blade part 3, is illustrated by dashed lines. The main blade part 3 is composed of a base body segment 3b and a trailing edge segment 3c. As can be seen at the upper end 5a of the main blade part 3, the base body segment 3b has a plurality of cavities 6 which, given sufficient strength, are used to reduce the blade mass in order to lower the mechanical and thermal stresses in operation. One or more cavities 6 may be filled wit...

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Abstract

The invention relates to a turbomachine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in said turbomachine. The aim of said invention is to develop a device and a method for the turbomachine making it possible to reduce the size of a radial split of the turbomachine in order to obtain greater degree of efficiency. The inventive turbomachine comprises a rotor rotationally mounted in the case of the turbomachine, a feeding channel embodied in the rotor for introducing a fluid and an outlet channel embodied in the rotor for removing said fluid. An inlet orifice of the feeding channel is disposed further inside than the outlet orifice of the outlet channel, and means influencing a liquid flow is formed of an actuating device dependent on centrifugal force. Methods for cooling the rotor only by decelerating the gas turbine and for heating the turbomachine rotor by heating fluid flowing therethrough are also disclosed.

Description

CROSS REFERENCE TO RELATED APPLICATION[0001]This application is the US National Stage of International Application No. PCT / EP2004 / 005753, filed May 27, 2004 and claims the benefit thereof. The International Application claims the benefits of European Patent application No. 03013857.2 EP filed Jun. 18, 2003, both of the applications are incorporated by reference herein in their entirety.FIELD OF THE INVENTION[0002]The invention relates to a blade for use in turbomachines, having a blade root, a platform region and a main blade part, which main blade part has a blade length from a blade leading edge to a blade trailing edge and a blade height from the platform region to a main blade part tip, and which is formed from at least one base body segment and, in the region of at least one of the two blade edges, from at least one edge segment which is connected in a positively locking manner to the base body segment.BACKGROUND OF THE INVENTION[0003]A corresponding turbine blade of modular co...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D5/14B23P15/04F01D5/28
CPCB23P15/04F01D5/14F05D2230/61F01D5/282F01D5/284F01D5/147
Inventor AHMAD, FATHIBUCHAL, TOBIASDANKERT, MICHAELLANG, GERNOTSCHEURLEN, MICHAEL
Owner SIEMENS AG
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