阅读说明：本技术 回收式喷射驱动 (Recovery type jet drive ) 是由 马丁.齐格勒 于 2018-05-28 设计创作，主要内容包括：本发明包括一种用于通过从推进流动中回收使用功率提高喷射驱动的效率的方法和装置。在螺旋桨壳体(5)中的由驱动机(9)经由驱动轴(1)驱动的外罩螺旋桨(4)从径流式涡轮(6)的内部空间(V<Sub>i</Sub>)输送用于喷射驱动的流体。流体轴向地加速且向后逆着行驶方向喷出。由此形成推力。因为在涡轮的内部空间中的压力降低，来自周围环境的新的流体直接经由旋转的径流式涡轮(6)的桨叶由外向内流动且由此驱动桨叶。没有导向器。径流式涡轮(6)的功率经由传动机构(2)传递到螺旋桨(4)的驱动轴(1)处，这减轻驱动机(9)的负担且提高喷射驱动的效率。本发明特别良好地适用于电驱动器。(The present invention includes a method and apparatus for improving the efficiency of an injection drive by recovering power from a motive flow. A shrouded propeller (4) in the propeller housing (5), which is driven by a drive machine (9) via a drive shaft (1), extends from the interior (V) of the radial turbine (6) i ) Delivering fluid for jet actuation. The fluid accelerates axially and is ejected backwards against the direction of travel. ByThis creates a thrust force. Because of the pressure reduction in the interior of the turbine, new fluid from the surroundings flows directly from the outside to the inside via the blades of the rotating radial turbine (6) and thereby drives the blades. There is no guide. The power of the radial turbine (6) is transmitted to the drive shaft (1) of the propeller (4) via the transmission (2), which reduces the load on the drive machine (9) and increases the efficiency of the jet drive. The invention is particularly well suited for use in electric drives.)

1. A method for improving the efficiency of jet drive by recovering the used power from the propulsion flow, characterized in that a shrouded propeller (4) in a propeller housing (5) driven by a drive machine (9) via a drive shaft (1) is driven from the inner space V of a radial turbine (6)_iConveying a fluid for said jet drive, said propeller (4) accelerating said fluid axially andthe jet is directed backwards against the direction of travel, new fluid flows from the surroundings directly from the outside to the inside via the blades of the rotating radial turbine (6) without a deflector and thereby drives the radial turbine (6), and the power of the radial turbine (6) is transmitted via a transmission (2) to the drive shaft (1) of the propeller (4), which reduces the load on the drive machine (9).

2. The method of claim 1, wherein the fluid is air.

3. The method of claim 1, wherein the fluid is water.

4. Method according to claim 1, characterized in that a part of the power is given directly from the radial turbine (6) to an open rotor (10), with its propeller blades (11) fixedly connected with the radial turbine, and the fluid from the surroundings is accelerated and thereby generates axial thrust.

5. Device for increasing the efficiency of jet drives by recovering the used power from the propulsion flow, characterized in that it contains a shrouded propeller (4) in a propeller housing (5) driven by a drive machine (9) via a drive shaft (1) and it contains a radial turbine (6) without a deflector, traversed by a fluid from the surroundings, wherein the fluid flows first through the radial turbine (6) and then through the propeller (4), and the radial turbine (6) is connected with a transmission (2), through which the power of the radial turbine is transferable to the drive shaft (1).

6. A device according to claim 5, characterized in that the drive machine (9) is an electric motor.

7. The device according to claim 5, characterized in that the drive machine (9) is a thermodynamic machine (gas turbine, piston motor).

8. Radial turbine (6) for an arrangement according to claim 5, characterised in that it has no guide, it is positioned between the fuselage (7) and the propeller housing (5), its axis of rotation is directed in the direction of travel, its blades follow the contour of a low-resistance flow body between the fuselage (7) and the propeller housing (5), their blades are profiled like an airfoil, the contour of the blades is twisted in the longitudinal direction, the twist of the contour increases from the front to the rear, and the ratio of the blade length to the mean contour depth is greater than 4 (the blades are significantly longer than the width).

9. Radial turbine (6) according to claim 8, wherein the diameter of the turbine rotor decreases from front to back.

10. Radial turbine (6) according to claim 8, characterized in that its axis of rotation is positioned coaxially to the propeller (4).

11. Radial turbine (6) according to claim 8, wherein the direction of rotation is opposite to the direction of rotation of the propeller (4).

12. Radial turbine (6) according to claim 8, characterized in that it comprises an open rotor (10) whose propeller blades (11) are fixedly connected to the radial turbine (6).

13. Device according to claim 5, characterized in that the transmission (2) comprises a direct force transmission, wherein the direct force transmission comprises a gear transmission or a planetary gear transmission.

14. Device according to claim 5, characterized in that the transmission mechanism (2) comprises an indirect force transmission, wherein the indirect force transmission comprises a magnetic, electromagnetic or flow-technical force transmission, wherein the magnetic force transmission comprises a permanent magnet, wherein the electromagnetic force transmission comprises a Wald-Lonnerd group or an electronically regulated electric motor/generator combination and wherein the flow-technical force transmission comprises an extended flow combination with a torque converter.

Technical Field

The present invention relates to a method and apparatus for improving the efficiency of jet actuation by recovering the used power from the motive flow. It is described as a drive for an aircraft, but can generally be used for drives of every type of vehicle. Including aircraft, land vehicles, and marine vessels.

Background

The jet drive according to the prior art delivers air or water by means of a propeller and generates a relatively high-speed jet which is ejected backwards against the direction of travel. The propeller is driven by a driver, which may be a heat engine or an electric motor. According to the usual injection theory, the thrust force is derived from the difference of the flow pulses at the equilibrium limit of the injection drive. This theory is based on newtonian law of force and thus thrust appears as a product of inertial forces (or reaction) from the acceleration of a stationary fluid. Thereby driving the vehicle.

The efficiency of the jet drive is the ratio of thrust power to power expended. Thrust power is the product of thrust multiplied by the speed of the vehicle. Which is required in order to move the vehicle through air or water. The power consumed is the mechanical shaft power for the propeller from the drive machine. Contained therein is the loss of kinetic energy in the jet-driven outflow (absctrom). There is additionally a heat loss from the drive machine.

The energy consumption of the jet drive is characterized by a thrust-specific power (schubspezifischeleisting), which is the drive power P per thrust F. It is measured in watts per newton, which is a speed. According to the rankine theory, the thrust-specific power of a simple jet drive is obtained as an arithmetic mean of the speeds of the inflow v and outflow c of the propeller. There are jet losses in the wake but no heat loss from the drive.

Power specific to rankine thrust (G1)

In order to improve the efficiency of the jet drive, the thrust-specific power thereof must be reduced. Mathematically, it means that the numerator of the fraction is reduced or the denominator thereof is increased. According to the theory of rankine, the additional power Δ P and the additional force Δ F therefore extend and:

extended thrust specific power (G2)

When the additional power Δ P is negative and the additional force Δ F is positive, the quotient

Is always less than the original value according to Rankine

. Then, precisely, the drive is more efficient than before. Thermodynamically, it is observed that the power is negative when it is given by the machine and used as the used power for the drive. When the force acts in the direction of motion, the force is positive.

The power used may be obtained by recovering energy from the propulsion flow. In the case of ships, a green guide wheel (Grimsche Leitrad) is known here, which uses an axial flow machine to recover energy in the wake of the ship propeller and to increase the efficiency of the drive. The disadvantage here is the interference between the propeller and the guide wheel, the high dynamic loading with all the blades and the loss of thrust at the main propeller. In the case of aircraft, it is not known to recover the use of power from the propulsive flow.

Disclosure of Invention

The object of the present invention is to find a method and a device with which the efficiency of the jet drive can be increased not only in the case of ships but also in the case of aircraft by recovering the power used from the propulsion flow. Here, the dynamic load from the propeller of the flow interference should be smaller than before. This object is achieved by a method according to claim 1 and an apparatus according to claim 4 and the following.

Drawings

The invention is described according to 5 figures:

1. as a view of the jet drive with all major components for a possible embodiment of the invention,

2. view of the principle of action for recovering energy from a propulsive flow,

3. a view of the flow forces at the rotor of a radial turbine,

4. an example of body integration for a drive.

5. With an example of power output to the open rotor.

Detailed Description

Jet-driven propellers generate a propulsive flow. The latter serves here to drive a radial turbine, the additional power of which is transmitted via a transmission to the drive shaft of the propeller. This reduces the burden on the drive motor. The radial turbine is designed such that the flow forces occurring at its blade blades have not only a force component F tangential to the direction of rotation_tAnd has an axial force component F in the direction of movement_x. The tangential component causes a torque at the radial turbine. Thereby forming an additional power ap. The additional thrust force af is formed from the axial force component.

Fig. 1 shows an embodiment of the new drive. The shrouded propeller (4) in the propeller housing (5) is driven by a drive machine (9) via a drive shaft (1) in the shaft channel (3). The drive shaft (1) is coupled to the radial turbine (3) via a transmission (2). The radial turbine (6) has no guide and is mounted on the shaft channel (3) via a ball bearing (8). Which rotates about a longitudinal axis between the fuselage (7) and the propeller housing (5). The blade wheel profile of which follows the shape of a low-resistance flow body between the fuselage (7) and the blade housing (5), wherein the rotor turnsThe minor diameter tapers from front to back. The propeller (4) conveys air from the inner space of the radial turbine (6) and generates a rearward jet. Thereby forming a thrust for advancing. Because of the pressure reduction in the interior of the radial turbine, the air flows through the rotating rotor from the outside and causes locally effective flow forces at its blades. Thereby forming additional power and additional thrust, and due to

The efficiency of the drive is improved.

Figure 2 shows the principle of recovery from the propulsive flow.

The main components are represented in fig. 2.1. The propeller (4) is driven by the drive shaft (1). Which is coupled to the rotor (6) of the radial turbine via a gear (2). The gear mechanism (2) is symbolized by the gear wheels present, wherein the gear mechanism can be implemented mechanically (e.g., planetary gear mechanism) or (electro-) magnetically (e.g., magnet gear mechanism, wold-lunard group, motor-generator with electronic control unit) or as a flow gear mechanism (extended flow unit with torque converter). Fluid flows from the ambient to the rotor without swirling. The given turbine power relieves the load on the drive machine. The propeller (4) and the turbine (6) rotate in opposite directions, which compensates for the torque from the drive.

Fig. 2.2 shows the occurring flow field. Volume V of propeller from inner space of rotor_iAir is delivered. Thereby, the pressure p is in_iAnd decreases. Due to the external pressure p_aAt this time, higher, the air forcibly flows from the outside and across the rotating blades of the radial turbine. A usable flow force is generated here.

FIG. 3 illustrates flow forces at a blade of a turbine rotor.

FIG. 3.1 shows a radial blade section (section coordinate x) at any point of the rotor_s) Consisting of a fuselage (ordinate x)₀) Extending up to the propeller housing (ordinate x)₁). Fig. 3.2 shows the position of the longitudinal section and the radial section from fig. 3.1.

In FIG. 3.1, it is presented thatInflow in radial blade cross-section. The inflow c to the turbine is effected in the radial direction without swirl. There is no guide. By superposition with the blade inflow u from the circumferential speed, a relevant inflow w is formed at the blade, which corresponds to the blade with the radius r_aThe tangent of the cross-sectional circle of (a) is inclined. The blade is profiled and twisted with respect to a tangent of the cross-sectional circle. The distortion of the contour increases from the front to the back. The rotor diameter is reduced here. The eccentrically acting lift force F is formed by the inflow of the blade cross section with the relative speed w_aThe line of action of which is inclined at an angle psi with respect to the radial direction and at a distance r from the axis of rotation_iAnd (5) stretching. Thereby, the lift force F_aAt a distance r_iCausing a torque M about the longitudinal axis. This results in a usable additional power Δ P, which reduces the load on the drive motor and reduces the numerator in equation (G2).

By means of the angle psi of inclination, the lift force F can be adjusted_aResolved into radial components F_rAnd a tangential component F_t. Radial component F_rActing against the centrifugal force from the rotation. Which reduces the burden on the blades of the blade. Component F of the tangential direction_tCausing torque for additional power.

In the longitudinal section according to fig. 3.2, the lift force F is shown_aInclination in the direction of flight. By tapering the rotor from front to back, a force component F in the direction of movement is formed in the local blade flow_x. This is an additional force Δ F that increases the denominator in equation (G2) and further improves efficiency.

In fig. 4, the drive is represented by way of example as an integral part of the aircraft fuselage. Which is located in the lee side of the fuselage. The propeller always draws its inflow from the inner space of the radial turbine. Here, an uneven potential energy drop is maintained during the entire journey (otherwise known as journey, Reise). Which has a local pressure and a local velocity at each spatial point. Thereby creating flow forces which cause additional thrust and additional power. Thereby, power is taken back from the propulsive flow flowing into the propeller, which is a recovery. The equation (G2) applies at this time, and the new drive may be more efficient than before, than according to simple theory of rankine.

In the case of a ship, the power used by the retrieval in the wake flow of the propeller is known as a green guide wheel. This is an axial flow machine. The power from the inflow is now recovered by means of a radial flow machine. A difference from known radial turbines is the lack of a guide.

The new principle of power recovery from the propulsive flow can be implemented with air or with water or with another fluid. The required power of the drive machine (9) can thereby be significantly reduced. The invention is particularly suitable for drives with an electric motor.

For lower speeds, it can be advantageous for the power of the radial turbine (6) to be transferred only to the propeller shaft (1) in a first portion. The second part can be directly exposed to the open rotor (10), the propeller blades (11) of which are fixedly connected to the radial turbine (6). In this case, the open rotor (10) is directly driven by the radial turbine (6).

One embodiment of such a configuration is shown in fig. 5. The open rotor (10) has a larger diameter than the radial turbine (6). The propeller blades (11) are fixedly connected with the radial turbine and generate axial thrust. In the case of lower speeds, this arrangement is advantageous, since the turbine power is given to the rotor with the larger diameter, which reduces the injection losses.

Reference symbols

1 drive shaft

2 drive mechanisms (mechanical, magnetic, fluid)

3-shaft channel

4 propeller

5 Propeller shell

6 radial turbine

7 fuselage

8 ball bearing

9 driver (thermodynamic machine or electric motor)

10 open type rotor (open rotor)

11 Propeller blade

Abbreviations and formula symbols

c injection speed (Rankine propeller theory)

c Absolute flow velocity (velocity triangle)

Thrust F

F₀Thrust according to rankine propeller theory

Additional force of Δ F

F_aLifting force

F_rForce component in radial direction

F_tComponent of force in tangential direction

F_xForce component in axial direction

M torque

p pressure

p_aExternal pressure, outside the radial turbine

p_iInternal pressure, inside the radial turbine

P drive power

P₀Drive power according to Rankine propeller theory

Delta P additional power

radius r

r_aOuter radius

r_iInner radius

u circumferential velocity (velocity triangle)

v cruise speed (Rankine propeller theory)

V_iVolume in the interior of a radial turbine

w relative flow velocity (velocity triangle)

x ordinate of the rotor section (x)_s=x₀..x₁)

Radial inclination angle of psi blade force.