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Multi-stage Turbo Compressor

A technology of turbo compressor and final pressure, applied in the direction of mechanical equipment, machine/engine, liquid fuel engine, etc., can solve the problem of damage to gas sealing devices, etc., to ensure work safety, suppress excessive consumption, and improve work safety Effect

Active Publication Date: 2012-11-28
SIEMENS ENERGY GLOBAL GMBH CO & KG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In this case, unfiltered, possibly moist process gas can reach the gas seal and damage it

Method used

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  • Multi-stage Turbo Compressor

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Embodiment Construction

[0015] figure 1 A multi-stage turbo compressor TC is shown, which includes six stages ST1 to ST6. Process gas PG enters each stage ST1 to ST6 and is compressed there from an inlet pressure p1 to p6 to a corresponding outlet pressure p2 to p7 . The individual stages ST1 to ST6 each have a rotor R on which the impellers of the stages ST1 to ST6 each formed as a radial compressor are arranged. The stages are each surrounded by a housing C, through the housing wall of which the shaft of the rotor R is guided for connection to a drive (not shown in detail). Gas seals DGS1 to DGS6 , which seal the respective stage end pressures p2 to p7 from the environment, are provided in the region of the passage. The gas seals DGS1 to DGS6 are respectively configured as dry gas seals and are supplied with sealing gas SG by means of sealing gas lines SGL1 to SGL6 . The gas seals DGS1 to DGS6 are each provided in a series arrangement, wherein on the pressure side a labyrinth seal is additionall...

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Abstract

The invention relates to a multi-stage turbo compressor (TC) which has at least one rotor (R) and a housing (C) and compresses a process gas (PG) from an inlet pressure (p1) at the inlet of a first stage (ST1) to an end pressure (p7) at the outlet (EX) of a last stage (ST6), wherein at least the first stage (ST1) and the last stage (ST6) are each allocated at least one gas seal (DGS1 - DGS6) that seals the passage of a rotor shaft through a wall of the housing (C) or seals the housing (C) with respect to a stage inlet pressure or stage end pressure, wherein the gas seals (DGS1 - DGS6) are connected to at least one sealing gas line (SGL1 - SGL6), by means of which they are supplied with sealing gas (SG). In order to create improved sealing of multi-stage turbo compressors that prevents gas seals from being subjected to unfiltered process gas, according to the invention at least one pressure chamber (PR) on the pressure side of the gas seal (DGS1 - DGS6) of the last stage (ST6), which provides sealing against the end pressure of the environment, is connected to at least one relief line (RL) ending in a pressure sink.

Description

technical field [0001] The invention relates to a multi-stage turbocompressor having at least one rotor and a casing, which compresses a process gas from an inlet pressure at the inlet of the first stage to a pressure at the outlet of the last stage Final pressure, wherein at least the first stage and the last stage are at least respectively equipped with a gas seal which seals outwardly the penetration of the rotor shaft through the wall of the housing, or with respect to the respective stage inlet pressure Or a stage final pressure outwardly sealed housing, wherein the gas seal is connected to at least one sealing gas line by means of which the gas seal is supplied with sealing gas. In the field of turbocompressors, gas seals, especially in series configurations, have the task of sealing the shaft passage from the pressure chamber in the housing against the atmosphere. Gas seals are contactless seals and are lubricated with dry, filtered sealing gas. The sealing gas is usu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/10F04D29/12
CPCF04D29/104F04D29/124
Inventor 卢德格尔·阿尔费斯
Owner SIEMENS ENERGY GLOBAL GMBH CO & KG