Inner wave-riding turbine-based combined power inlet with binary variable geometry

A turbine-based combination and air inlet technology, which is applied in the direction of jet propulsion devices, gas turbine devices, machines/engines, etc., can solve the problems of not being able to meet the working Mach number range, etc., and achieve simple and reliable deformation, fulfillment of requirements, and good airflow quality Effect

Active Publication Date: 2016-08-24
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 the flow, the existing inner waverider inlet is mainly for high-speed fixed geometry, which cannot meet the wide working Mach number range

Method used

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  • Inner wave-riding turbine-based combined power inlet with binary variable geometry
  • Inner wave-riding turbine-based combined power inlet with binary variable geometry
  • Inner wave-riding turbine-based combined power inlet with binary variable geometry

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Embodiment

[0037] Designed a variable geometry inlet suitable for internal parallel TBCC combined power with a working Mach number range of 0-4 and a transition Mach number of 2.5. Due to the maximum operating Mach number of 4.0, a combination of sub-fuel ramjet and turbo engine is adopted. Adopting the internal multiplier type air inlet method to design the air inlet profile when the maximum working Mach number is 4.0. Therefore, the selected design parameters of the ICFC basic flow field: 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 a length-to-height ratio of 1.6, and the center point of the flow field of the inlet is arranged at the center under the rectangular inlet. A simple and adjustable variable geometry scheme is designed based on the M4 basic profile. Attached figure 1 A three-dimensional schematic diagram of the entire internal parallel TBCC inle...

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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 internal multiplier type turbine-based combined cycle (Turbine Based Combined Cycles, TBCC) air inlet and a binary curved surface variable geometry design method, belonging to the technical field of high-speed air inlets. Background technique [0002] With the rapid development of air-breathing aircraft, hypersonic aircraft has become the main strategic development direction of future aircraft. Its flying range is very wide, and the flying Mach number has expanded from subsonic, transonic, and supersonic speeds to hypersonic speeds. Because different types of engines have their own advantages in different flight ranges, many countries in the world have carried out research to try to integrate different engines in their respective advantages to form a combined cycle propulsion system, so that the aircraft can work in the entire range The internal performance is optimized. At present, there are more researches on RBCC (rocket-base...

Claims

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Application Information

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Patent Type & Authority Patents(China)
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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