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Hybrid exhaust turbofan engine propulsion system introduced into parallel combustion chamber

A turbofan engine and propulsion system technology, which is applied in jet propulsion devices, gas turbine devices, machines/engines, etc., can solve problems such as low combustion rate and unstable combustion, and achieve the effect of increasing exhaust gas temperature

Inactive Publication Date: 2020-10-16
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

In order to solve the problem that the gas temperature in front of the turbine is too high due to the increase of the specific thrust of the turbofan engine, and other component materials cannot bear it, and it also avoids the disadvantages of unstable combustion and low combustion rate caused by the secondary combustion method , to further improve the thrust characteristics of the turbofan engine

Method used

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  • Hybrid exhaust turbofan engine propulsion system introduced into parallel combustion chamber
  • Hybrid exhaust turbofan engine propulsion system introduced into parallel combustion chamber
  • Hybrid exhaust turbofan engine propulsion system introduced into parallel combustion chamber

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Embodiment Construction

[0041] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0042] For the convenience of description, words such as "first end" and "second end" used in this application are used to describe the relative positional relationship, and the "left side" of the flow direction in the current view is taken as the "first end" and "right end". Side" is the "second end"; and the "upper" of the current view is the "first end" and "lower" is the "second end"; it can be understood that the use of the above words should not be interp...

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Abstract

The invention relates to the field of energy and power machinery in the aviation industry, in particular to a hybrid exhaust turbofan engine propulsion system introduced into a parallel combustion chamber. The system can improve the thrust characteristics of a turbofan engine, and specifically comprises an inner duct formed from a fan and a mixer; an outer duct is also formed from the fan to the mixer; a high-pressure air compressor and a first combustion chamber are arranged on the inner duct; the high-pressure air compressor and the first combustion chamber are sequentially connected to thedownstream part of the fan; when the fan is in work, external air can be sucked via an air feeding channel; the high-pressure air compressor is used for pressurizing the external air to form first airso that a part of the first air moves along the flow direction of the inner duct; besides, the external air can enter the outer duct via the fan so that the other part of air can reach the mixer, andthus the external air can enter a second combustion chamber when moving along the flow direction of the outer duct. From an energy prospective, the system can transmit internal energy of a fuel to the outer duct in order to increase the temperature of exhaust air.

Description

technical field [0001] The invention relates to the technical field of energy and power systems in the aviation industry, in particular to a propulsion system of a mixed-exhaust turbofan engine introduced into parallel combustion chambers. Background technique [0002] Among the current methods of energy and power systems in the aviation industry, the widely recognized method is to adopt the Brayton cycle. The Brayton cycle is characterized by high flexibility, reliability, simple structure, and fast startup and loading speed. Therefore, it is widely used in the current method. It is a reliable technology for aviation power system. [0003] At present, due to the limitations of technology and materials, the performance of traditional turbofan engines based on Brayton cycle is close to its theoretical limit. Existing aircraft have put forward higher requirements on the thrust or economy of the engine. Based on this, the subject of research and development work tends to propo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K3/11F02K3/06F02C3/14F02K1/38
CPCF02C3/14F02K1/386F02K3/06F02K3/11
Inventor 徐国强孙京川闻洁全永凯郭昆庄来鹤刘启航
Owner BEIHANG UNIV
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