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Gas turbine assembly and method for operating said gas turbine assembly

A gas turbine and unit technology, applied to engine components, machines/engines, mechanical equipment, etc., can solve problems such as separation changes

Pending Publication Date: 2022-06-28
ANSALDO ENERGIA SWITZERLAND AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the separation can vary due to thermal expansion and mechanical backlash depending on the operating conditions of the gas turbine components

Method used

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  • Gas turbine assembly and method for operating said gas turbine assembly
  • Gas turbine assembly and method for operating said gas turbine assembly
  • Gas turbine assembly and method for operating said gas turbine assembly

Examples

Experimental program
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Embodiment Construction

[0046] exist figure 1 In reference numeral 1 refers to the gas turbine assembly (in figure 1 shown schematically).

[0047] The gas turbine assembly 1 includes a compressor 3 , a combustor 4 , and a turbine 5 .

[0048] In particular, the gas turbine assembly 1 includes a stator 6 defining at least a compression working channel 8 and an expansion working channel 9 .

[0049] The compressor 3 and the turbine 5 are mounted on the same shaft to form a rotor 11 which is housed in the stator 6 and extends along the axis A.

[0050] In more detail, the rotor 11 includes a front axle 12 , a plurality of rotor stages 13 and a rear axle 14 .

[0051] Each rotor stage 13 includes a rotor disk 16 and a plurality of rotor blades 17 coupled to the rotor disk 16 and arranged radially.

[0052] A plurality of rotor discs 16 are arranged in succession between the front axle 12 and the rear axle 14 and are preferably sandwiched into a stack by a central tie rod 18 . Alternatively, the rot...

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Abstract

The invention relates to a gas turbine assembly and a method for operating the gas turbine assembly, and provides a gas turbine assembly extending along a longitudinal axis, comprising: a stator defining a working passage; a rotor comprising a plurality of rotor stages; each rotor stage includes a plurality of blades rotatable in a working channel about a longitudinal axis; each blade is provided with a tip; at least one movable element coupled to the stator by means of at least one holding device and radially moved between the stator and at least one tip of the blade to adjust the clearance; wherein the movable element is coupled to the stator by means of a holding device in order to create an adjustment gap between the stator and the movable element in fluid communication with the working channel; the movable element is provided with at least one first sealing element which divides the adjusting gap into at least two chambers; the first chamber is in fluid communication with the working passage upstream of the rotor stage, and the second chamber is in fluid communication with the working passage downstream of the rotor stage.

Description

[0001] CROSS-REFERENCE TO RELATED APPLICATIONS [0002] This patent application claims priority from European Patent Application No. 20217259.9, filed on December 24, 2020, the entire disclosure of which is incorporated herein by reference. technical field [0003] The present invention relates to gas turbine assemblies and to methods for operating the same. In particular, the gas turbine assembly of the present invention may be part of an apparatus for producing electrical energy. Background technique [0004] As is known, gas turbine assemblies for power plants include compressors, combustors, and turbines. [0005] In particular, the compressor includes an inlet to which air is supplied and a plurality of rotating blades through which the air is compressed. The compressed air leaving the compressor flows into the plenum, ie the closed volume bounded by the outer casing, and from there into the combustor. The compressed air is mixed with at least one fuel within the com...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D11/16
CPCF01D11/16F05D2240/56
Inventor T·齐尔C·J·布里考德H-P·博斯曼
Owner ANSALDO ENERGIA SWITZERLAND AG