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Turbomachine comprising means for improving cooling of rotor disc by means of air flow

A technology of rotor wheel and turbine engine, which is applied to components of pumping devices for elastic fluids, mechanical equipment, air transportation, etc., and can solve problems such as increased wear of wear-resistant materials, low cooling flow rate, and increased clearance of aircraft

Active Publication Date: 2020-11-17
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This results in a low flow rate of the cooling flow at the bottom of the rotor disk, causing high response times at the critical point of the gap
The result is increased wear on wear-resistant materials and increased clearance when the vehicle operates in cruise mode

Method used

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  • Turbomachine comprising means for improving cooling of rotor disc by means of air flow
  • Turbomachine comprising means for improving cooling of rotor disc by means of air flow
  • Turbomachine comprising means for improving cooling of rotor disc by means of air flow

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Embodiment Construction

[0041] figure 1 A part of the elements of a turbine engine is shown through which the main flow passes, especially the high-pressure body, and then the low-pressure turbine. Here, the high-pressure body includes a high-pressure compressor 1, a combustion chamber 2 and a high-pressure turbine 3. The gas of the main flow F leaving the high-pressure turbine 3 drives the low-pressure turbine 4. The main flow F reaches the high-pressure compressor 1 through an annular duct 5, which usually connects the high-pressure compressor 1 to a low-pressure compressor located upstream (not shown here). The high-pressure compressor 1 includes a plurality of rotor wheels 6 that are fixed to the rotor wheel 7 of the high-pressure turbine 5 and rotate at a given speed ω1 around the axis X of the engine.

[0042] In particular, the rotor wheels 6 of the high-pressure compressor 1 each have a disk 8 which carries on its outer periphery an annular row of blades working in the main flow F. The disk 8 ...

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Abstract

The invention concerns an aircraft turbomachine comprising at least one tubular element (12), such as a rotor shaft, and at least one rotor wheel extending around the tubular element (12) and comprising a disk (8b) carrying, at the outer periphery of same, an annular row of blades, said disk (8b) extending at a radial distance h from said tubular element (12) in such a way as to define an annularflow space for a cooling gas flow (Fr) during operation. The turbomachine is characterized in that the tubular element (12) comprises at least one annular wall (19) extending radially outwards and configured to divert said gas flow (Fr) in order for it to pass substantially radially between the disk (8b) and this annular wall (19).

Description

Technical field [0001] The invention relates to aircraft turbine engines. More specifically, the object of the present invention is to control the clearance between the rotor and the stationary parts in the compressor and the turbine, especially during the operation of the turbine engine. Background technique [0002] The prior art especially includes documents WO-A1-2015 / 050680, US-A1-2016 / 069193, GB-A-836952 and US-A1-2016 / 024927. [0003] In the compressor and in the turbine, the clearance at the top of the moving wheel has a first-order effect on the efficiency of the engine. The gap is mainly the result of mechanical and thermal phenomena. [0004] The main mechanical phenomena are: the deformation of the rotor under centrifugal force, the influence of pipeline pressure on the rotor and stator, and the axial displacement. [0005] Regarding thermal phenomena, we have found that, especially in high-pressure compressors, there is a difference in the expansion of the components of...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/08F01D11/24F04D29/58
CPCF01D5/186F01D5/081F01D5/082F01D11/24F04D29/584F05D2240/40F05D2240/61F05D2260/221F04D29/321Y02T50/60F05D2220/323
Inventor 克里斯托弗·朔勒斯
Owner SAFRAN AIRCRAFT ENGINES SAS