Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner

A turbine-based combination and air inlet technology, which is used in jet propulsion devices, gas turbine devices, machines/engines, etc., can solve problems such as the inability to meet the working Mach number range, and achieve simple and reliable deformation, good airflow quality, and requirements. Effect

Active Publication Date: 2015-05-20
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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AI Technical Summary

Problems solved by technology

Although the inner waverider inlet with the technical feature of direct streamline tracking has been proved to be able to capture 100% of

Method used

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  • Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner
  • Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner
  • Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner

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Embodiment

[0037] A variable geometry intake port is designed for the internal parallel TBCC combination power suitable for the working Mach number range of 0-4 and the transitional Mach number of 2.5. Since the maximum working Mach number is 4.0, a combination of a sub-combustion ramjet engine and a turbine engine is adopted. The inlet profile at the maximum working Mach number 4.0 is designed by using the inner waverider inlet method. Therefore, the design parameters of the ICFC basic flow field are selected: M1=4.0, M3=1.4, and the initial internal contraction angle is 10°. The design requirements for the shape of the inlet are: the outlet of the inlet is a regular rectangle with an aspect ratio of 1.6, and the center point of the flow field of the inlet is arranged at the center of the lower side of the rectangular inlet. Based on the basic profile of M4, a simple and adjustable variable geometry scheme is designed. attached figure 1 A three-dimensional schematic diagram of the en...

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Abstract

The invention discloses an internal waverider-derived turbine base combined dynamic gas inlet adopting a binary variable-geometry manner. The internal waverider-derived turbine base combined dynamic gas inlet structurally comprises a gas inlet internal waverider compression section 1, a throat section 2, an expansion and distribution section 3, a punching channel 4, a turbine channel 5, a fixed-geometry three-dimensional internal waverider compression representing section 6, an adjustable internal waverider compression representing section 7, an adjustable internal waverider compression section representing variable-geometry compression surface 8, an adjustable expansion representing section 9, a sharp point-free distribution representing section 10, a machine body proximity representing movable upper arm 11, a movable upper arm driving representing servo action cylinder 12, a distribution representing plate 13, an internal waverider-derived fixed-geometry representing profile 14 and a distribution representing cross section 15. The internal waverider-derived turbine base combined dynamic gas inlet has the advantages of small outer resistance, high flow coefficient, good airflow quality and the like; meanwhile, profile deformation and distribution plate deflection caused by compression in a three-dimensional internal waverider manner can be controlled by only two regulating parameters, the deformation is convenient and reliable, and the requirement on an acting servo device is relatively easily met.

Description

technical field [0001] The invention relates to an inner waveriding type turbine-based combined power (Turbine Based Combined Cycles, TBCC) inlet port and a variable geometry design method of a binary curved surface, belonging to the technical field of high-speed inlet ports. Background technique [0002] With the rapid development of air-breathing aircraft, hypersonic aircraft has become the main strategic development direction of future aircraft. Its flight range is very wide, and its flight Mach number extends from subsonic, transonic, supersonic to hypersonic. Because different types of engines have their own advantages in different flight ranges, many countries in the world have carried out research, trying to integrate different engines in their respective advantages to form a combined cycle propulsion system, so that the aircraft can operate in the entire operating range. Internal performance is optimal. At present, there are two kinds of RBCC (rocket-based combined ...

Claims

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Application Information

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IPC IPC(8): F02C7/042
Inventor 黄国平左逢源夏晨陈杰黄慧慧
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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