CN104481696B - The empty dual-purpose motor of a kind of contrarotating purchasing ore water - Google Patents

Abstract

The invention discloses a counter-rotating exoskeleton water-air dual-purpose engine. The main structure of the engine includes: a support frame, an oil and electricity pipeline, a front thrust bearing, a circumferential bearing, a fairing, an inner duct, an outer duct, and a compressed air Engine, annular combustion chamber, turbine, rear thrust bearing, converging tail nozzle, central duct, inner rotor, outer rotor, blade tongue and groove, fan, engine cover, power transmission pipeline, conductive slip ring, oil pipeline, converging channel , rotary joint, metal fuel chamber, metal-water reaction combustion chamber, fan vane. The compressor and turbine of this engine have no stator blades. In the air working state, the outer frame rotor and the inner rotor counter-rotate, so that both the compressor and the turbine are counter-rotating. This improves the engine efficiency while reducing the absolute rotational speed of the rotor and shortening the axial direction of the engine. size, reducing structural weight. When working in water, the annular combustion chamber does not work, the inner and outer rotors are stationary, and the power is generated by the metal-water reaction combustion chamber to realize water jet propulsion.

Description

A counter-rotating exoskeleton water-air dual-purpose engine

technical field

The invention belongs to the field of aero-engines, and in particular relates to a counter-rotating outer frame water-air dual-purpose engine.

Background technique

An aero-engine is a highly complex and precise thermodynamic machine. As the heart of the aircraft, the aero-engine is known as the "flower of industry", which directly affects the performance, reliability and economy of the aircraft. With the advancement of technology, aircraft put forward higher and higher requirements for aero-engines, such as higher thrust-to-weight ratio, lower fuel consumption rate, higher reliability, better maintainability, longer life, and lower overall life Cycle costs, wider scope of work, etc.

The compressor and turbine blades of traditional aero-engines are divided into rotor blades and stator blades. The stator blades are fixed on the casing, and the rotor blades are installed on the shaft, which rotates with the shaft during operation. This traditional structural design is increasingly unable to meet the requirements of advanced aircraft engines, such as higher thrust-to-weight ratio and smaller structural size. So counter-rotation technology came into being. The counter-rotation means canceling the stator blades, and the adjacent rotor blades are counter-rotating. In theory, counter-rotating technology can greatly reduce the number of compressor and turbine blade stages, thereby greatly reducing the structural weight and structural size of the engine. At present, the relatively successful application is the counter-rotating turbine technology, such as the F119 engine of Pratt & Whitney Company. However, due to the large number of blade stages of the compressor, it is difficult to realize the counter-rotation technology. At present, there is no engine example that successfully uses the compressor counter-rotation technology in the world.

With the proposal of the US Integrated High Performance Turbine Engine Technology (IHPTET) program, the concept of a new structure engine with an exoskeleton has also entered the public eye. The biggest difference between the exoskeleton engine proposed by NASA and the traditional engine is that the central rotating shaft is cancelled, the stator blades originally fixed on the casing are designed and installed on the inner stator layer, and the rotating parts are replaced by the outer rotor layer. Both the machine and turbine rotor blades are suspended on the outer rotor layer, and only the outer rotor layer rotates during operation. Experiments have proved that the exoskeleton structure can greatly improve the structural efficiency of the engine and reduce the structural weight by about 30%, thereby greatly increasing the thrust-to-weight ratio and reducing fuel consumption. However, due to the large moment of inertia when the outer rotor rotates, the engine speed is limited, and at the same time, higher requirements are placed on the bearings. This kind of structural design is still in the experimental verification stage.

Future warfare puts forward requirements for multi-habitation operations of aircraft, which can not only fly in the air, but also quickly dive underwater to avoid the enemy's search and attack, especially for future ocean-going combat aircraft. Such performance is required. In order to realize the amphibious aircraft, it is necessary to have an engine capable of amphibious use. At present, several forms of amphibious engines have been proposed in the world, but many difficulties have been encountered in the development process, making the amphibious The engine is still in the test verification stage.

Contents of the invention

The object of the present invention is to provide a counter-rotating exoskeleton water-air dual-purpose engine, which aims to improve the structural efficiency and thrust-to-weight ratio of the aero-engine, reduce the structural weight, reduce the structural size, reduce the absolute rotational speed of the rotor, and simultaneously realize air and water Continuous work under two different working conditions.

The present invention is achieved in this way. A counter-rotating exoskeleton water-air dual-purpose engine mainly includes a support frame, oil and electricity pipelines, a front thrust bearing, a circumferential bearing, a fairing, an inner duct, an outer duct, and a compressed air Engine, annular combustion chamber, turbine, rear thrust bearing, converging tail nozzle, central duct, inner rotor, outer rotor, blade tongue and groove, fan, engine cover, power transmission pipeline, conductive slip ring, oil pipeline, converging channel , rotary joint, metal fuel cavity, metal-water reaction combustion chamber and fan vane; it is characterized in that: the front support frame of the engine is fixedly placed in the engine cover, and the support frame is cross-shaped when viewed from the windward side of the engine, and the engine The cover and the rear support frame of the engine are fixedly placed on the engine mounting frame of the aircraft;

The outer rotor layer is installed on the support frame through the front thrust bearing, the rear thrust bearing and the circumferential bearing, and can rotate around the axis;

The inner rotor layer is installed on the support frame through the front thrust bearing, the rear thrust bearing and the circumferential bearing, and can rotate around the axis;

The inner channel is located inside the outer rotor layer and outside the inner rotor layer, and is a circulation channel surrounded by the inner and outer rotor layers;

The outer duct is located inside the engine cover and outside the outer rotor layer, and is a circulation channel surrounded by the engine cover and the outer rotor layer;

The central duct is the circulation channel located inside the inner rotor layer;

The oil and electricity pipeline is buried inside the engine cover and the front support frame of the engine, and enters the inner rotor layer from the aircraft main body through the engine cover and the front support frame from top to bottom;

The fairing is fixedly placed on the front support frame of the engine, located in front of the front thrust bearing of the inner rotor layer, similar to a trumpet-shaped structure, the purpose is to adjust the airflow (water flow) and protect the front thrust bearing and circumferential bearing behind it. , conductive slip rings, rotary joints and other structures;

The compressor blades and the turbine blades are fixedly mounted on the tenon and groove, and the tenon and groove are distributed on the inner side of the outer rotor layer and the outer side of the inner rotor layer;

The fan blades are fixed on the tongue and groove on the outer side of the outer rotor layer;

The vane of the fan is fixedly installed inside the engine cover, suspended from the outside to the inside, and a circumferential bearing is installed on the top of the blade, which contacts the inner rotor layer and plays a certain supporting role;

The power transmission pipeline is branched from the end of the oil and electricity pipeline buried inside the support frame at the front of the engine, bypassing the circumferential bearing, and its end is connected to the stator end of the conductive slip ring. The power transmission pipelines located inside the inner rotor layer are laid axially, and multiple lines are laid along the circumference, the beginning of which is connected to the rotor end of the conductive slip ring, and the ends respectively enter the annular main combustion chamber and the metal-water reaction engine;

The conductive slip ring is divided into a stator end and a rotor end. The stator end is fixed at the end of the power transmission line protruding from the front support frame of the engine, and the rotor end is fixedly installed outside the inner rotor layer and circles the inner rotor layer. The stator end is in contact with and connected to several transmission pipelines laid inside the inner rotor layer. The electricity passes through the power transmission line separated from the oil-electricity line laid inside the front support frame of the engine, reaches the stator end of the conductive slip ring, and conducts to the rotor end through contact, and then enters the power transmission line inside the inner rotor layer;

The oil pipeline is branched from the end of the oil and electricity pipeline buried inside the support frame at the front of the engine, bypassing the circumferential bearing, and its end is connected with a rotary joint. The oil delivery pipeline located inside the inner rotor layer is laid axially, and multiple lines are laid along the circumference, the beginning of which is connected to a circle of annular grooves on the outside of the inner rotor layer, and the end is connected to the annular main combustion chamber;

The swivel joint is fixed to the end of the oil delivery pipeline branched from the oil and electricity pipeline embedded in the front support frame of the engine, and is a stationary circular ring structure. Its width along the axial direction of the engine matches with an annular groove on the outer side of the inner rotor layer, and a brush seal is set between the annular groove wall;

The annular combustion chamber is fixedly installed on the subsidiary structure of the inner rotor layer, and can rotate together with the inner rotor layer;

The converging channel structure is fixedly installed on the outer rotor layer and can rotate accordingly. The converging structure helps to form an airflow converging channel, and a brush-type sealing structure is arranged between the annular combustion chamber and the annular combustion chamber to maintain the total pressure;

The converging tail nozzle is fixedly installed on the inner rotor layer, forming a converging channel to help the gas enter the outlet guide vane and finally leave the engine, and at the same time protect the circumferential bearing and the rear thrust bearing from being affected by high temperature gas;

The metal fuel chamber is one of the components of the metal-water reaction engine. The metal fuel cavity is fixedly installed in front of the concave cavity inside the inner rotor layer;

The metal-water reaction combustion chamber is one of the components of the metal-water reaction engine, and is located at the rear of the concave cavity inside the inner rotor layer, where water and metal fuel react.

The advantages of the present invention are:

(1) Compared with traditional aero-engines, this design cancels the central rotating shaft and the stator blades of the compressor and turbine, and replaces them with inner and outer rotor layers, so that both the compressor and the turbine can achieve counter-rotation, so that under the condition of satisfying the pressure ratio It can greatly reduce the number of compressor and turbine blade stages, reduce the axial structural size of the engine, reduce the structural weight, significantly increase the thrust-to-weight ratio of the engine, and reduce the absolute rotational speed of the rotor. At the same time, it is equipped with a metal-water reaction combustion chamber, and the central duct is used as a medium channel when working in water, realizing dual-use of water and air.

(2) Compared with the existing counter-rotating engines, this design realizes the counter-rotating multi-stage compressors on the basis of the counter-rotating turbines, which has not been realized in traditional counter-rotating engines. Therefore, the thrust-to-weight ratio of the engine can be further improved, the structural weight can be reduced, and the fuel consumption rate can be reduced.

(3) Compared with the exoskeleton concept engine proposed by NASA, this design integrates its advantages, that is, the central rotating shaft is canceled, the outer rotor layer blade suspension has lower material requirements, the structural weight is reduced, and the structural efficiency is improved. At the same time, the inner stator layer is improved to make it an inner rotor layer to achieve counter-rotation with the outer rotor layer, thereby reducing the number of stages of compressor and turbine blades, reducing the absolute speed of the inner and outer rotors, reducing the requirements for bearings, and further reducing the structure. Reduce the weight, reduce the axial dimension, increase the thrust-to-weight ratio, and reduce the fuel consumption rate.

Description of drawings

Fig. 1 is the main schematic diagram of the overall structure of the contra-rotating exoskeleton water-air engine of the present invention.

Fig. 2 is a schematic diagram of the conductive slip ring and oil-electric pipeline of the present invention (detail A in Fig. 1).

In the figure, 1 is the support frame, 2, the oil and electricity pipeline, 3, the front thrust bearing, 4, the circumferential bearing, 5, the fairing, 6, the internal channel, 7, the external channel, 8, the compressor, 9 , annular combustion chamber, 10, turbine, 11, rear thrust bearing, 12, convergent tail nozzle, 13, central duct, 14, inner rotor, 15, outer rotor, 16, blade tongue and groove, 17, fan, 18 , engine cover, 19, power transmission pipeline, 20, conductive slip ring, 21, oil pipeline, 22, convergence passage, 23, rotary joint, 24, metal fuel chamber, 25, metal-water reaction combustion chamber, 26, static fan leaf.

detailed description

Below in conjunction with accompanying drawing this design is further described.

As shown in Figure 1, a counter-rotating exoskeleton water-air dual-purpose engine, the main structure of the engine includes: (1) support frame, (2) oil and electricity pipeline, (3) front thrust bearing, (4) Circumferential bearing, (5) fairing, (6) inner duct, (7) outer duct, (8) compressor, (9) annular combustor, (10) turbine, (11), rear thrust bearing, ( 12) Converging tail nozzle, (13) Central duct, (14) Inner rotor, (15) Outer rotor, (16) Blade tongue and groove, (17) Fan, (18) Engine cover, (19) Power transmission line , (20) Conductive slip ring, (21) Oil pipeline, (22) Convergence channel, (23) Rotary joint, (24) Metal fuel chamber, (25) Metal-water reaction combustion chamber, (26) Fan vane; It is characterized by:

The engine front support frame (1) is fixedly arranged in the engine cover (18), and the engine cover (18) and the engine rear support frame (1) are fixedly arranged on the engine mounting frame of the aircraft. The outer rotor layer (15) is installed on the support frame (1) through the front thrust bearing (3), the rear thrust bearing (11) and the circumferential bearing (4), and can rotate around the axis. The inner rotor layer (14) is installed on the support frame (1) through the front thrust bearing (3), the rear thrust bearing (11) and the circumferential bearing (4), and can rotate around the axis.

The compressor blades (8) and the turbine blades (10) are fixedly mounted on the tenon grooves (16), and the tenon grooves are distributed on the inner side of the outer rotor layer (15) and the outer side of the inner rotor layer (14). The fan blades (17) are fixedly mounted on the tongue and groove on the outer side of the outer rotor layer (15). The annular combustion chamber (9) is fixedly installed on the subsidiary structure of the inner rotor layer (14), and can rotate together with the inner rotor layer (14). The converging channel structure (22) is fixedly mounted on the outer rotor layer (15) and can rotate accordingly. The converging structure (22) helps to form an airflow converging channel, and a brush-type sealing structure is arranged between the annular combustion chamber (9) to maintain the total pressure. The converging tail nozzle (12) is fixedly installed on the inner rotor layer (14), forming a converging channel to help the gas enter the outlet guide vane and finally leave the engine, while protecting the circumferential bearing (4) and the rear thrust bearing (11) from high-temperature gas influences.

Accompanying drawing 2 shows how the oil-electric pipeline (3) enters the inner rotor layer (14) from the front support frame (1). Oil and electricity pipelines (3) are buried in the front support frame (1) from the fuselage via the engine cover (18). When the pipeline is close to the installation position of the inner rotor layer, the circumferential bearing (4) is bypassed and the power transmission pipeline (19) is separated first, through a conductive slip ring (20) fixedly installed on the outer side of the inner rotor layer (14) and Several circuits buried in the inner rotor layer (14) along the axial direction are connected, and finally enter the annular main combustion chamber (9) ignition device and the metal-water reaction combustion chamber (25). For the fuel channel, lay several fuel pipelines (21) inside the inner rotor layer (14) in advance, and form a circle of grooves along the circumference at the front fuel inlet to connect the preset fuel pipelines (21). After the pipe comes out of the support frame (1), the fuel is input into the groove through the rotary joint structure (23) and enters each oil delivery pipeline (21), and finally enters the combustion chamber. The gap between the rotary joint structure (23) and the inner rotor layer (14) uses a brush seal to prevent fuel leakage.

Under the working state in the air, the outer rotor layer (15) and the inner rotor layer (14) counter-rotate, and the metal-water reaction combustion chamber (24) does not work. Part of the air flow passes through the central duct (13) unimpeded, part of it enters the outer duct (7) and leaves the engine through the fan (17), and part of it enters the inner duct (6), and passes through the convergence channel after the compressor (8) does work on it The structure (22) enters the annular combustion chamber (9) for combustion, and the high-temperature and high-pressure gas is ejected from the combustion chamber (9) to drive the turbine (10) to do work, thereby driving the inner rotor layer (14) and the outer rotor layer (15) to rotate. After passing through the turbine (10), the gas passes through the converging tailpipe (12) and then leaves the engine through the outlet guide vanes. In this way, the continuous operation of the engine in the air is realized.

Under the working state in water, the annular main combustion chamber (9) stops working and closes the air inlet to prevent water from entering. The metal-water reaction combustion chamber (25) enters the working state, water enters the reaction zone along the central duct (13), and at this time, the active metals (sodium, potassium, lithium, etc.) stored in the metal fuel chamber (24) are sprayed by the nozzle It reacts with water to produce a large amount of hydrogen and energy, and the reaction product is sprayed out along the channel to achieve continuous water jet propulsion.

Claims (1)

1. the empty dual-purpose motor of contrarotating purchasing ore water, this motor mainly comprises: supporting frame, oily fulgurite road, front thrust bearing, circle bearing, cowling, main duct, by-pass air duct, gas compressor, annular combustion chamber, turbine, rear thrust bearing, convergence jet pipe, central duct, internal rotor, external rotor, blade tongue-and-groove, fan, engine hood, transmission of electricity pipeline, conducting slip ring, pipeline road, convergent passage, swivel joint, metallic fuel chamber, metal-water reaction firing chamber and Fan Stator; It is characterized in that:

Support frame as described above is fixedly mounted in engine hood, and engine hood and motor back support frame are fixedly mounted on the motor mounts of aircraft;

Described external rotor is arranged on supporting frame by front thrust bearing, rear thrust bearing and circle bearing, and can around axis rotation;

Described internal rotor is arranged on supporting frame by front thrust bearing, rear thrust bearing and circle bearing, can around axis rotation;

Namely described main duct is positioned at inside external rotor, outside internal rotor, by inner and outer Rotator around circulation passage;

Namely described by-pass air duct is positioned at inside engine hood, outside external rotor, by engine hood, external rotor around circulation passage;

Namely described central duct is positioned at the circulation passage of internal rotor inside;

Described oily fulgurite road is embedded in engine hood and supporting frame is inner, from top to bottom enters internal rotor through engine hood, supporting frame from aircraft body;

Described cowling is fixedly mounted on motor front support frame, and before being positioned at internal rotor, thrust bearing is anterior;

The blade of described gas compressor and key building block blade and turbine is fixedly loaded on tongue-and-groove, and tongue-and-groove is distributed in inside external rotor and outside internal rotor;

Described fan is fixedly loaded on the tongue-and-groove outside external rotor;

Described Fan Stator is fixedly installed in inside engine hood, and ecto-entad hangs, and at vane tip, circle bearing is housed, and contacts with internal rotor;

The oil electricity line end that described electroduct route is embedded in supporting frame inside separates, walk around circle bearing, its end is connected to the stator end of conducting slip ring, the electroduct curb being positioned at internal rotor inside is axially laid, and circumferentially lay many, its top connects conductive sliding ring rotor end, and end enters annular main combustion chamber and metal-water reaction firing chamber respectively;

Described conducting slip ring is divided into stator end and rotor-end, stator end is fixed on the end of the transmission of electricity pipeline stretched out by motor front support frame, rotor-end is fixedly mounted on outside internal rotor layer, enclose around internal rotor layer one, with stator end in contact, and be connected to several transmission of electricity pipelines being laid on internal rotor layer inside, the transmission of electricity pipeline that electricity branches away through the oily fulgurite road being laid on motor front support frame inside, arrive conducting slip ring stator end, and conduct to rotor-end by contact, enter the transmission of electricity pipeline of internal rotor layer inside;

Described pipeline road is separated by the oil electricity line end being embedded in supporting frame inside, walk around circle bearing, its end is connected to swivel joint, the pipeline road being positioned at internal rotor layer inside is laid vertically, and circumferentially lay many, its top is communicated with the ring annular groove outside internal rotor layer, and end is connected to annular main combustion chamber;

The pipeline road end that described swivel joint and the oily fulgurite road being embedded in supporting frame inside separate is fixed, it is the circular shape structure that a circle is static, its along engine shaft to width, match with the ring annular groove outside internal rotor, and and between annular groove wall, brush seal is set;

Described annular combustion chamber is fixedly mounted on the accessory structure of internal rotor layer, can rotate with internal rotor layer;

Described convergent passage is fixedly mounted on external rotor, can rotate thereupon, and convergence structure helps to form air-flow convergent passage, and is provided with brush seal structure between annular combustion chamber to keep stagnation pressure;

Described convergence jet pipe is fixedly mounted on internal rotor, and formation convergent passage helps combustion gas to enter exit guide blade and finally leaves motor, protects circle bearing and rear thrust bearing not to affect by high-temperature fuel gas simultaneously;

Described metallic fuel chamber is one of constituent element of metal-water reaction motor, and the cavity that metallic fuel chamber is fixedly mounted on inside internal rotor layer is anterior;

Described metal-water reaction firing chamber is one of constituent element of metal-water reaction motor, and be positioned at the cavity mid-rear portion inside internal rotor, water and metallic fuel react herein.