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Convergent-divergent adjustment tab pair for nozzle of variable geometry turbojet engine, adjustment tabs each comprising cooling air circulation duct

A geometric shape and turbojet technology, applied in engine manufacturing, engine function, machine/engine, etc., can solve problems such as increased cooling demand and increased gas temperature, and achieve the effect of improving mechanical durability

Active Publication Date: 2022-04-12
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] However, this aim contradicts the desire to increase the reheat gas concentration to improve the propulsion performance of the turbojet engine, since such an increase in concentration involves an increase in the temperature of the gas, and therefore an increase in the need for cooling

Method used

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  • Convergent-divergent adjustment tab pair for nozzle of variable geometry turbojet engine, adjustment tabs each comprising cooling air circulation duct
  • Convergent-divergent adjustment tab pair for nozzle of variable geometry turbojet engine, adjustment tabs each comprising cooling air circulation duct
  • Convergent-divergent adjustment tab pair for nozzle of variable geometry turbojet engine, adjustment tabs each comprising cooling air circulation duct

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Embodiment Construction

[0045] figure 1Illustrated is a turbojet engine 10 for the propulsion of an aircraft capable of supersonic flight, such as a twin-spool turbofan engine, and is therefore particularly intended for their installation in the fuselage of such an aircraft.

[0046] Throughout the description, the axial direction X is the direction of the longitudinal axis 11 of the turbojet. Unless otherwise specified, the radial direction R is the direction perpendicular to and passing through the longitudinal axis 11 at all points, and the circumferential direction C is the direction perpendicular to the radial direction R and the longitudinal axis at all points. 11 Orthogonal directions. Unless otherwise specified, the terms "inner" and "outer" refer to the relative proximity and relative distance of an element with respect to the longitudinal axis 11, respectively. Finally, the adjectives “upstream (of)” and “downstream (of)” are defined with reference to the general direction D of the gas fl...

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PUM

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Abstract

In a convergent-divergent regulation tab pair (52B) for a variable geometry convergent-divergent type turbojet engine nozzle (28), a convergent regulation tab (40B) and a divergent regulation tab (42B) comprise respective cooling air ducts (70, 78) connected to each other to be able to cool each regulation tab. The duct of the divergence adjustment sheet includes an impingement cooling cavity defined by two lateral end walls provided with vent openings through which the impingement cooling cavity leads to the outside.

Description

technical field [0001] The present invention relates to the field of turbojet engines for the propulsion of aircraft capable of supersonic flight, and more particularly to a pair of convergent-divergent flaps for the nozzle of a turbojet engine of the variable geometry convergent-divergent type , a nozzle equipped with such a convergent-divergent flap pair, and a turbojet engine comprising such a nozzle. Background technique [0002] Turbojet engines for supersonic flight usually comprise a reheat channel, the outlet of which is defined by an axisymmetric nozzle of the convergent-divergent type, in order to allow acceleration of the air flow leaving the reactor to velocities greater than Mach 1. [0003] In order to be effective at the various speeds at which supersonic vehicles are capable of flying, such nozzles have a variable geometry, allowing the internal cross-section of the nozzle to be varied, and in particular the position and shape of the throat of the nozzle . ...

Claims

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Application Information

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IPC IPC(8): F02K1/12F02K1/82
CPCF02K1/1223F02K1/822F05D2260/201F02K3/10Y02T50/60F05D2220/323F05D2240/128F05D2250/323F05D2250/324
Inventor 弗朗索瓦·莱格雷弗洛伦特·吕克·拉孔贝皮埃尔·安德烈·加布里埃尔·马尔博伊斯西尔万·马塞尔·奥布拉扎蒂埃里·科恩
Owner SAFRAN AIRCRAFT ENGINES SAS