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Axial turbine for a gas turbine with limited play between blades and housing

A technology for axial flow turbines and gas turbines, which is applied to the supporting elements of blades, machines/engines, mechanical equipment, etc., can solve the problems of reducing the power density and efficiency of gas turbines, and achieve the effect of reducing gap flow

Inactive Publication Date: 2011-06-15
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

As a result, a radial gap of corresponding size temporarily exists at the blade tip, which leads to a reduction in the power density and efficiency of the gas turbine

Method used

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  • Axial turbine for a gas turbine with limited play between blades and housing
  • Axial turbine for a gas turbine with limited play between blades and housing
  • Axial turbine for a gas turbine with limited play between blades and housing

Examples

Experimental program
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Embodiment Construction

[0025] Such as Figures 1 to 3 As shown, an axial turbine 1 has a rotor blade 2 with a leading edge 3 and a trailing edge 4 . The rotor blade 2 has a pressure side 5 and a suction side 6 which each extend from a leading edge 3 to a trailing edge 4 . The pressure side 5 is curved more concavely than the suction side 6 . At its radially outer end, the rotor blade 2 has a blade tip 13 which is free standing. In the region of the blade tip 13 , the rotor blade 2 is designed in a “front load design” 7 . In contrast, a “rear load design” 8 is shown, in which the pressure side 5 is less curved in the region of the front edge 3 than in the “front load design” 7 .

[0026] Since the rotor blade 2 is configured in the region of the blade tip 13 in a “rear load design” 7 , the region 9 with the greatest pressure load of the rotor blade 2 is located in the region of the blade tip 13 in the vicinity of the leading edge 3 .

[0027] Furthermore, the axial turbine 1 has a hub profile 10 ...

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PUM

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Abstract

The invention relates to an axial turbine (1) for a gas turbine comprising a rotor blade cascade that is formed from rotor blades (2) having, respectively, a front edge (3) and a radially outer, free-standing (13) blade tip, and an annular space wall (11) that surrounds the rotor blade cascade and that has an annular space inner side (12), enabling the annular space wall to be arranged directly adjacent to the blade tip forming a radial gap between the covering of the blade tip and the annular space inner side. The invention is characterised in that the blade tips are designed aerodynamically such that when the axial turbine is in operation, the area of the blade tip with the highest pressure load is disposed in the region of the front edges, and the rotor blades in the region of their front edges have a radial elevation (16) and the annular space wall comprises, on the annular space inner side, a peripheral radial recess (15) that interacts with the radial elevations such that a gap width minimum is established in the direction of the main through flow of the axial turbine when seen in the region of the front edge.

Description

technical field [0001] The invention relates to an axial turbine for a gas turbine, wherein the axial turbine has low clearance losses. Background technique [0002] Gas turbines have, for example, turbines of axial flow design. The turbine has a casing and a rotor surrounded by the casing. The rotor has a shaft on which shaft power is output. A hub is arranged around this shaft, the contour of which together with the inner contour of the housing forms a flow channel through the turbine. Due to the mostly conical inner contour of the housing, this flow channel has a cross section that expands in the direction of flow. [0003] The rotor has a plurality of rotor stages, each of which is formed by a rotor cascade. The rotor blade grid has a plurality of rotor blades, which are fastened with one end to the rotor on the hub side and point radially outward with the other end. A blade tip is formed on the other end of the rotor blade, which blade tip faces the inner side of t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/20F01D5/14
CPCF01D5/20F01D5/143F01D5/141
Inventor S·布劳恩C·科内利厄斯A·海洛斯O·海因T·霍夫鲍尔A·埃姆德C·莱尔纳S-U·马丁T·马泰斯R·梅斯根E·舒曼R·特特鲁克A·齐默曼
Owner SIEMENS AG