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Nacelle for a bypass turbomachine comprising a thrust reverser, bypass turbomachine comprising such a nacelle, and aircraft comprising at least one such turbomachine

A dual-duct, aircraft technology, applied in the field of aircraft, can solve problems such as large debris and turbine damage

Pending Publication Date: 2021-11-23
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] However, the use of thrust reversers only allows the speed of the aircraft to exceed a predetermined speed limit, such as 60 knots (111.12 km / h)
Below this speed limit, the risk of the turbine re-ingesting the airflow from the thrust reverser exhaust upstream of the nacelle is too great, and in addition, the risk of ingesting debris thrown by the thrust reverser exhaust airflow from the runway is too great, both Conditions that could cause damage to the turbine

Method used

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  • Nacelle for a bypass turbomachine comprising a thrust reverser, bypass turbomachine comprising such a nacelle, and aircraft comprising at least one such turbomachine
  • Nacelle for a bypass turbomachine comprising a thrust reverser, bypass turbomachine comprising such a nacelle, and aircraft comprising at least one such turbomachine
  • Nacelle for a bypass turbomachine comprising a thrust reverser, bypass turbomachine comprising such a nacelle, and aircraft comprising at least one such turbomachine

Examples

Experimental program
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no. 2 example

[0158] According to a second embodiment, the actuating mechanism is designed to:

[0159] - selectively maintaining the second cascade 23 in the retracted position and by sliding the movable cowl 14 and the first cascade 15 on the one hand along the longitudinal axis 104 from the closed position to the open position and from the retracted position, respectively sliding to the extended position and on the other hand sliding along the longitudinal axis respectively from the open position to the closed position and from the extended position to the retracted position to selectively move the movable cowl and the first cascade;

[0160] - selectively maintaining the first cascade 15 in the retracted position and by sliding the movable cowl 14 and the second cascade 23 on the one hand along the longitudinal axis 104 from the closed position to the open position and from the retracted position, respectively Sliding to the extended position and on the other hand sliding along the long...

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PUM

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Abstract

The invention relates to a nacelle (10A) for an aircraft bypass turbomachine (100), comprising: - an annular envelope (11) extending about a longitudinal axis (104), - a thrust reverser (13) comprising: o an annular movable cowl (14) situated downstream of the annular envelope and able to slide with respect to the annular envelope along the longitudinal axis between a closed position and an open position in which the cowl and the nacelle casing define an opening between one another, o at least one first thrust reverser cascade (15), o an actuating mechanism designed to allow a partial or total thrust-cancelling configuration of the thrust reverser, in which configuration the movable cowl is moved into its open position while maintaining the or each first cascade in its retracted position, the opening (17) being occupied by at least one second thrust-attenuating cascade (23) of the thrust reverser, in such a way that the secondary flow passing through the opening exits to the outside of the nacelle with a speed oriented so as to generate a substantially zero or positive thrust along the longitudinal axis.

Description

technical field [0001] The invention relates to a nacelle for a double-duct turbine comprising a thrust reverser, a double-duct turbine comprising such a nacelle, and an aircraft comprising at least one such turbine. Background technique [0002] Typically, an aircraft dual-duct turbine includes a fan for sucking in an airflow that is divided downstream of the fan into a primary airflow and a secondary airflow, the primary airflow flowing in a main flow channel called a main flow path inside the core of the turbine, The secondary air flow bypasses the core in secondary flow channels called secondary flow paths. [0003] In the main flow path, the primary airflow flows through the low-pressure compressor, high-pressure compressor, combustor, high-pressure turbine, low-pressure turbine, and exhaust nozzle in an upstream-to-downstream direction. In the secondary flow path, the secondary airflow may flow through the guide vane assembly. [0004] Both primary and secondary airf...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D29/06F02K1/72F02K1/76
CPCB64D29/06F02K1/72F02K1/763F02K1/766B64D2033/0286Y02T50/60
Inventor 纪尧姆·格莱玛瑞克昆汀·马蒂亚斯·伊曼纽尔·加诺德
Owner SAFRAN AIRCRAFT ENGINES SAS