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A power turbine inlet guide for a combustion-driven compressor unit

A compressor unit and power turbine technology, applied in the direction of machines/engines, mechanical equipment, engine components, etc., can solve the problems of poor realizability, long axial dimension, complex structure, etc., to reduce the loss of aerodynamic performance, increase the number, The effect of simplifying the structure

Active Publication Date: 2022-01-11
中船重工龙江广瀚燃气轮机有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The purpose of the present invention is to solve the problems of complex structure, long axial dimension, large loss and poor realizability existing in the existing turbine inlet guide

Method used

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  • A power turbine inlet guide for a combustion-driven compressor unit
  • A power turbine inlet guide for a combustion-driven compressor unit
  • A power turbine inlet guide for a combustion-driven compressor unit

Examples

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specific Embodiment approach 1

[0026] Specific implementation mode one: combine Figure 1 to Figure 4 Describe this embodiment, a power turbine inlet guide for a combustion drive compressor unit in this embodiment includes a guard ring 2, a guide vane set 3 and a guide vane set pressure ring 4, and it also includes an isolation cover 5, an inner casing 7, The casing 1 and the cooling system, the inner casing 7 is set on the isolation cover 5, the casing 1 is set on the outside of the inner casing 7 and connected to the inner casing 7 through the guide vane group 3, and the lower part of the guide vane group 3 is passed through the guide vane The group pressure ring 4 is press-fitted on the isolation cover 5, the upper part of the guide vane group 3 is press-fitted on the casing 1 through the retaining ring 2, and the cooling system is installed in the casing 1, the guide vane group 3, and the inner cover from top to bottom. On the casing 7 and the isolation cover 5; the casing 1 is a casing with a large mer...

specific Embodiment approach 2

[0028] Specific implementation mode two: combination figure 1 Description of this embodiment, the casing 1 of this embodiment includes a diffuser section 1-1, a gentle section 1-2 and a grommet installation section 1-3, and a diffuser section 1-1, a gentle section 1-2 and a grommet installation Segments 1-3 are sequentially connected from left to right and integrated. Such setting can not only reduce the axial dimension of the guide, but also facilitate the installation of the guide vane group and other equipment and parts, avoiding the sudden increase of the expansion angle of the diffuser section, causing other existing guide vanes to Inconvenience in design, manufacturing, craftsmanship, and assembly caused by the inability to install leaf groups and other components. Other compositions and connections are the same as in the first embodiment.

specific Embodiment approach 3

[0029] Specific implementation mode three: combination figure 1 To describe this embodiment, the included angle between the diffuser section 1 - 1 and the axis in this embodiment is 41°-43°. With such arrangement, the axial dimension of the guide is shortened under the premise of ensuring the connection between the gas generator turbine and the power turbine. Other compositions and connections are the same as those in Embodiment 1 or Embodiment 2.

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Abstract

The utility model relates to a power turbine inlet guide for a combustion-driven compressor unit, which relates to a power turbine inlet guide. The invention aims to solve the problems of complex structure, long axial dimension, large loss and poor realizability existing in the existing turbine inlet guide. The inner cover (7) of the present invention is set on the isolation cover (5), the casing (1) is set on the outside of the inner cover (7) and connected with the inner cover (7) through the guide vane group (3), and the guide The vane group (3) is press-fitted on the lower part of the isolation cover (5) through the guide vane group pressure ring (4), and the guide vane group (3) is press-fitted on the upper part of the isolation cover (5) through the guard ring (2). The cooling system Set on the casing (1), guide vane group (3), inner casing (7) and isolation cover (5) in turn from top to bottom; the casing (1) is a large meridian expansion angle casing, and the casing ( 1) The shape of the flow passage between the inner shell (7) and the inner casing (7) is S-shaped. The present invention uses combustion to drive the compressor unit.

Description

technical field [0001] The invention relates to a power turbine inlet guide. In particular, it relates to a power turbine inlet guide used for connecting a gas generator turbine and a power turbine with a large meridional expansion structure for a combustion drive compressor unit, with relatively short axial dimensions and low loss. Background technique [0002] Gas turbines have the characteristics of high power density and rapid response, and are widely used in power generation, mechanical drives and other fields. Modern gas turbines are developing in the direction of high power, high efficiency, and high stability and reliability. High-performance and high-reliability power turbines are an important guarantee for gas turbines' work economy, safety, and function realization. [0003] Gas turbines used in natural gas pipelines to drive compressor units usually adopt a structure with a power turbine. The gas generator turbine speed of this gas turbine is much higher than th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D9/04F01D25/14
CPCF01D9/041F01D25/145
Inventor 林枫牛夕莹马涛林洪飞李宗全李国强
Owner 中船重工龙江广瀚燃气轮机有限公司
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