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A turbine and method of collecting airflow in a turbine

A technology of turbines and air flow, applied in the direction of machines/engines, gas turbine devices, components of pumping devices for elastic fluids, etc., to achieve the effect of reducing mass and reducing head loss

Active Publication Date: 2022-08-02
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The patent does not address structures that include a downstream compressor disk that includes a central hole that allows airflow to flow therein
In addition, it is not the object of this patent to provide air flow collecting pipes that deliver the air flow to the central hole

Method used

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  • A turbine and method of collecting airflow in a turbine
  • A turbine and method of collecting airflow in a turbine
  • A turbine and method of collecting airflow in a turbine

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Embodiment Construction

[0038] refer to Figure 4 , Figure 4 A turbine with a gas flow collection loop is shown in accordance with an embodiment of the present invention.

[0039] As previously mentioned, the turbine extends longitudinally along the X-axis and includes a main duct V in which the gas flow F flows from upstream to downstream. In the following, the terms "upstream" and "downstream" are defined with respect to the X-axis extending from upstream to downstream. The terms "longitudinal" and "radial" are defined relative to the X-axis, the term "radial" is more precisely defined in a plane transverse to the X-axis. Similarly, the terms "inner" and "outer" are defined radially with respect to the X-axis.

[0040] In this embodiment, the turbine includes a compressor 100, a combustor, and a turbine from upstream to downstream.

[0041] refer to Figure 4 , in a known manner, the compressor 100 comprises an upstream compressor disk 1A, a downstream compressor disk 1B and a gas flow collec...

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Abstract

The invention discloses a turbomachine extending longitudinally along the X-axis and comprising a main duct (V) in which a gas flow (F) flows from upstream to downstream, the turbomachine comprising at least one upstream compressor disk (V) 1A), at least one downstream compressor disc (1B) and for the concentrated gas flow (F) from the main duct (V) p ) in the airflow collection circuit that collects the airflow, and the airflow collection circuit includes a radial portion (CP 1 ) and longitudinal section (CP 2 ), radial part (CP 1 ) is installed with at least one airflow collecting pipe (4), the longitudinal section (CP 2 ) extending between the cylinder (5) and the central bore (13) of the downstream compressor disc (1B), the turbine comprising a plurality of vanes (6) in the longitudinal section (CP) of the airflow collection circuit 2 ) and is configured to rotate about the X-axis to drive the concentrated airflow (F p ).

Description

technical field [0001] The present invention relates to a turbine and a method of collecting airflow in a turbine. Background technique [0002] refer to figure 1 , in a known manner, the turbine T extends longitudinally along the X axis and enables the airflow F to flow in the annular main duct V from upstream to downstream. In the following, the terms "upstream" and "downstream" are defined with respect to the X-axis extending from upstream to downstream. The terms "longitudinal" and "radial" are defined relative to the X-axis, with the term "radial" being more specifically defined in a plane transverse to the X-axis. Similarly, the terms "inner" and "outer" are defined radially with respect to the X-axis. [0003] The turbine T includes a compressor 100, a combustor, and a turbine in which the airflow F flows from upstream to downstream. The compressor 100 includes a plurality of compressor discs in a known manner. like figure 2 As shown, the turbine includes a gas...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/32F04D29/58F01D5/00
CPCF01D5/082F01D11/001F02C6/08F04D29/321F04D29/582F05D2240/126F01D5/12F05D2260/20
Inventor 克里斯多夫·斯科尔特斯于利斯·雅克·伯纳德·丹特尼
Owner SAFRAN AIRCRAFT ENGINES SAS
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