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Radial turbomachine

A turbine, radial flow technology, used in mechanical equipment, engine components, machines/engines, etc., can solve problems such as damage to seals, seals no longer

Inactive Publication Date: 2017-05-10
EXERGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In this way, there is a risk of damaging the seal so that it can no longer function properly and provide the turbine with the designed performance

Method used

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  • Radial turbomachine
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  • Radial turbomachine

Examples

Experimental program
Comparison scheme
Effect test

example 1

[0167] Example 1— Figure 10 -current technology

[0168] This example involves prior art and is shown in Figure 10 structure in which the annular rotor joint 22 (using the same reference numerals as the present invention for easier comparison) is constrained to the rotor disk 2 in such a way that the annular rotor joint cannot freely move radially under the action of centrifugal force Expansion (there is practically no annular band 23 with finite thickness). The third rotor and the fourth stator are mounted in such a way that the distance between the end of the plate 31 and the surface facing this end is 0.38 mm both in cold (turbine off) and hot (running turbine) conditions .

example 2—

[0169] Example 2— Figure 6A -this invention

[0170] It can be seen that the structure of the sealing device (plate 31 facing the non-grooved surface) is similar to that of Figure 10 The structure is the same, but in this case the presence of the annular band 23 enables the radial expansion of the assembly consisting of the rotor joint 22 , the rotor blade 3 and the end rotor ring 24 .

[0171] The third rotor and the fourth stator are mounted in such a way that the distance "V2" between the end of the plate 31 and the surface facing this end is 0.7 mm in cold conditions (turbine stopped). When the turbine is running, this distance "V2" decreases to about 0.38mm.

example 3—

[0172] Example 3— Figure 6 -this invention

[0173] In this example, the radial expansion of the assembly formed by the rotor joint 22 , the rotor blade 3 and the end rotor ring 24 causes insertion of the ends of the plates 31 into the corresponding slots 29 .

[0174] The third rotor and the fourth stator are mounted in such a way that the distance "V2" between the end of the plate 31 and the radially outer surface of the rotor joint 22 and from the end rotor ring 24 is in cold conditions (turbine stopped) About 0.2mm. When the turbine is running, the plate is inserted into the slot 29 to a depth "P" of approximately 0.12 mm. Furthermore, during operation, the distance "V1" between the end of the plate 31 and the bottom of the groove 29 is about 0.38 mm.

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Abstract

The present invention relates to a radial turbomachine, comprising: a fixed casing (6); at least one rotor disc (2,2') installed in the casing (6) and rotatable in the casing (6) around a respective rotation axis (X-X); a plurality of annular rotor elements (3,22,23,24; 22,23) coaxial with the rotation axis (X-X), axially projecting from a front face (4,4') of the rotor disc (2,2') and / or from a rear face (9,9') of the rotor disc (2,2'); a plurality of annular fixed elements (13,25,27; 34) coaxial with the rotation axis (X-X), axially projecting from the casing (6) and each positioned in a radially external position with respect to a respective annular rotor element (3,22,23,24; 22,23); a plurality of sealing devices (28,29; 29,31; 32,33) radially interposed between at least some of said annular rotor elements (3,22,23,24; 22,23) and the respective annular fixed elements (13,25,27; 34). The annular rotor elements (3,22,23,24; 22,23) are radially movable between a first radially contracted configuration, when the turbomachine (1) is in a non-operative condition, wherein, at the sealing devices (28,29; 29,31; 32,33), the annular rotor elements (3,22,23,24; 22,23) are radially spaced from the respective annular fixed elements (13,25,27; 34), and a second radially expanded configuration under the action of the centrifugal force and / or of the heat, when the turbomachine (1) is operating, wherein, at the sealing devices (28,29; 29,31; 32,33), the annular rotor elements (3,22,23,24; 22,23) are close to the respective annular fixed elements (13,25,27; 34). In the second configuration the sealing devices (28,29; 29,31; 32,33) substantially prevent the passage of a working fluid between the annular rotor elements (3,22,23,24; 22,23) and the annular fixed elements (13,25,27; 34).

Description

technical field [0001] The object of the invention is a radial turbine. A radial turbine refers to a turbine with which the flow of a fluid exchanging energy is directed mainly in a radial direction with respect to the axis of rotation of said turbine. The invention applies to both the driving turbine (turbine) and the working turbine (compressor). [0002] Preferably, but not exclusively, the invention relates to an expansion turbine of the radial type for generating electrical and / or mechanical energy. [0003] Preferably, but not exclusively, the present invention relates to radial expansion turbines for use in plants for generating energy by steam Rankine cycle or Organic Rankine cycle (ORC). [0004] Preferably, but not exclusively, the invention relates to expansion turbines of the centrifugal radial or "outflow" type, the term "outflow" meaning that the fluid flow is directed radially from the center towards the periphery of the turbine. Background technique [000...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/04F01D11/00
CPCF01D5/041F01D11/001F05D2230/60F05D2230/70
Inventor C·斯帕达奇尼D·里齐
Owner EXERGY