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Nozzle for turbine, turbomachine turbine equipped with said nozzle and turbomachine equipped with said turbine

一种涡轮机、喷嘴的技术，应用在机器/发动机、机械设备、发动机元件等方向，能够解决密封片脱离、耗时、影响等问题

Active Publication Date: 2021-09-07
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0012] The implementation and manufacture of the seal groove 207 and the installation of the inter-section seals are very costly and time consuming
The size of the groove 207 is also difficult to determine and there is a high risk that the seal disc will break away from the seal groove 207 and get lost in the air duct, with the result that air leaks and may affect other parts of the turbine

Method used

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  • Nozzle for turbine, turbomachine turbine equipped with said nozzle and turbomachine equipped with said turbine
  • Nozzle for turbine, turbomachine turbine equipped with said nozzle and turbomachine equipped with said turbine
  • Nozzle for turbine, turbomachine turbine equipped with said nozzle and turbomachine equipped with said turbine

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Embodiment Construction

[0042] The nozzle according to the invention is referenced 4 and comprises an annular collar 5 on which a plurality of angled nozzle segments 6 are fixed. Nozzle 4 is only partly in Figure 9 is visible in .

[0043] Now, will combine Figure 2 to Figure 4 The annular collar 5 is described in more detail. The annular collar extends through 360° and has a longitudinal axis X1-X'1.

[0044] The annular collar 5 comprises a cylindrical ring portion 50 (or tube) having a minimum width relative to its diameter, a minimum thickness and having a longitudinal axis X1-X′1.

[0045] The ring 50 has a radially inner surface 51 and a radially outer surface 52 .

[0046] as from Figure 7 , Figure 8 and Figure 11Seen more clearly, the inner surface 51 carries a wear resistant material 53 made of one or more elements. Preferably, the wear-resistant material 53 is a honeycomb structure. This abradable material 53 is brazed to the ring 50 and renewed by machining as previously desc...

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PUM

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Abstract

The invention concerns a turbine nozzle, comprising a plurality of angular nozzle sectors (6) each angular sector (6) comprising two inner and outer platform sectors, connected together by a plurality of radial blades (63), each inner platform sector (62) being rigidly attached to a radially inner foot (621), this nozzle comprising an annular collar (5) on which the nozzle angular sectors are fastened end-to-end circumferentially, this collar (5) comprising a cylindrical ring (50) the radial inner face (51) of which comprises an abradable material (53). This nozzle is characterised in that the radially inner foot (621) of each inner platform sector comprises a radial tab (622) and in that the annular ring (50) comprises a plurality of L-shaped pads (55), each pad delimiting a slot (553) for receiving the tab (622), so as to ensure the fastening by coupling of the collar on each nozzle angular sector.

Description

technical field [0001] The invention relates to a nozzle for a low-pressure turbine or a high-pressure turbine, a low-pressure turbine or a high-pressure turbine comprising a nozzle and a turbomachine comprising such a turbine, such as an aircraft turbojet or turboprop. Background technique [0002] Some turbines include a low-pressure turbine and a high-pressure turbine that recover some of the energy released by fuel combustion to drive a low-pressure compressor and a high-pressure compressor, respectively, located in the air inlet region of the turbine. [0003] attached figure 1 A multistage 10 low pressure turbine 1 is shown, from upstream to downstream with respect to the flow direction of air in the turbine (arrow V: i.e. at figure 1 From left to right in the figure), each stage 10 successively comprises a nozzle 2 and a rotor wheel 3 . All rotors are fixed on shafts, not shown in the figures, and at the same time the shafts are driven in rotation. [0004] The low...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/04F01D11/00
CPCF01D9/041F01D11/001F05D2260/33F01D9/04F01D11/125F05D2220/323F05D2240/128F05D2240/55
Inventor 科拉莉·辛西娅·格拉德哈姆扎·盖西恩
Owner SAFRAN AIRCRAFT ENGINES SAS
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