Patent Grant
10634047
The present disclosure relates to a technology field of turbine and compressor of turbojet, and specifically to a multiple axle-sleeve driving bidirectional rotating wheel-shaped fan turbine and a bushing wheel-shaped fan compressor.
An existed working mode of a turbine and a compressor of a turbojet engine (a core engine) is as follows. Multi-stage fans of the compressor rotate in order to compress air concentrated from 10 times to more than 20 times and convey the air to the combustor and mix the air with a fuel. The mixed gas is ignited in the combustor and is exploded out from the rear of the engine and in the meanwhile drives to rotate the multi-stage fans of the turbine. Multi-stage fans of the turbine provide power for multi-stage fans of the compressor through a single or a plurality of driving shafts (double shafts or triple shafts), so that the turbojet works. In general, if more air is compressed and conveyed by the compressor of the turbojet engine, a compression ratio is higher, a thrust of the turbojet engine is greater, a thrust-weight ratio is higher, an efficiency is higher, and more energy consumption is saved. However, there has been a few outstanding problems in the existing turbojet engine at present. Firstly, problems of fans: a fan blade of the fan is connected with the single shaft and multiple shafts in a cantilever structure. The fan blade is vulnerable to deform under a circumstance of wind pressure. In addition to an effect of thermal expansion on the fan blade, a certain space is allowed to ensure an avoidance of a friction and collision between working stages of the fans (axial direction) or between a fan tip and an inner duct (radial direction). However this certain space induces an escape of the compressed gas, reducing a working efficiency of the compressor. A stage of the fan of the compressor has to be increased in order to improve the compression ratio, thereby increasing a weight of the turbojet engine. Or, the fan blade is improved to have a wider chord, a thicker fan blade and a bigger root. In fact, the wide chord fan blade increase a working resistance as well as weight, thus becoming a burden during the air entering into the turbojet engine, and reducing a working efficiency and the thrust-weight ratio of the turbojet engine, when a velocity of a flying airplane is over the supersonic speed. Secondly, heat-resisting problem of the material. The fan at the last stage is too vulnerable to lose its strength and be melted or be corroded if the compression ratio reaches a certain degree. The increase of the compression ratio leads to a consequent increase of temperature of a mixed air, when the mixed gas is ignited in the combustor and exploded to the rear of the turbojet engine. Therefore, the compression ratio is restricted and thus the working efficiency is restricted. Thirdly, surging of the turbojet engine. Since the single driving shaft or multiple driving shafts drive the rotation of the multiple stage of fans, a last stage fan is stalled induced by a stalling of a first stage fan due to a resistance of air inflow, so that the turbojet engine works disorderly or even stops working.
In order to improve the working efficiency of the turbojet engine (the core engine), and minimize the problems restricting the efficiency which are mentioned above, the present disclosure discloses a multiple axle-sleeve driving bidirectional rotating wheel-shaped fan turbine and a bushing wheel-shaped fan compressor. It includes a working component, a driving component, a structural and installed component and a starting component.
Wherein, the working component comprises a plurality of wheel-shaped fans, and the wheel-shaped fans are formed by an internal tapered ring, an external tapered ring and a plurality of fan blades for connecting the internal tapered ring and the external tapered ring.
The wheel-shaped fans are divided into a plurality of wheel-shaped fans of the compressor and a plurality of wheel-shaped fans of the turbine. And the wheel-shaped fans of the compressor consist of a plurality of main wheel-shaped fans (indicated as 11, 12, 13, 14, 15, 16, 17, 18, 19 in
A front part of a first main wheel-shaped fan of the compressor (indicated as 11 in
The first main wheel-shaped fan of the compressor (indicated as 11 in
A fan blade of each of the wheel-shaped fans of the turbine (indicated as 49, 48, 47, 46, 45, 44, 43, 42, 41 in
The rim (indicated as Xa in
Wherein round ball bearings as well as a slide way (indicated as Xd in
The wheel hub (indicated as Xc in
Wherein a plurality of driving key grooves or driving keys (indicated as Xe in
A wheel hub of the auxiliary wheel-shaped fan is bushed on a wheel hub of corresponding main wheel-shaped fan, and swinging key grooves or swinging keys (indicated as Xf in
A plurality of driving key grooves or driving keys (indicated as Xg in
A starting gear ring (indicated as 19h in
A rolling ratchet (indicated as 19k in
The rim of each of the wheel-shaped fans coincides with a central axis of the corresponding wheel hub of each of the wheel-shaped fans.
A fan blade (indicated as Xb in
One end of the fan blade is provided perpendicular to a tangent line of a connecting point of an internal side the rim, and the other end of the fan blade is provided perpendicular to a tangent line of a connecting point of an external side the wheel hub.
The connecting point between the rim and the fan blade and the connecting point between the fan blade and the wheel hub are not on a same radical emitted from a center of the wheel-shaped fan. The fan blade has a “S” shape (indicated as 15b, 25b or 45b in
Beneficial effects of the wheel-shaped fan of the working component in present disclosure are as follows compared to the prior art. Firstly, the structure of the wheel-shaped fan improves a fixing mode of the fan blade. An existing unilateral and fixed connection between a fan blade and a driving axle with a cantilevered force structure, is replace by a bilateral and fixed connection of the fan blade and the rim as well as the fan blade and the wheel hub. An anti-bending moment of inertia of the fan blade improves multiple times. Deformation by force greatly reduces, which may induce a reduction on the thickness of the fan blade and on a weight of a root structure. Additionally, working resistance is also deceased and air leakage is reduced by decreasing an axis space between the wheel-shaped fans to reduce leakage (and a small amount of leakage forms a film to reduce a rotation friction between the wheel-shaped fans). Additionally, no air leakage exists between the tip of the wheel-shaped fan and the outer duct in an integrated body of the rim, the wheel hub and the fan blade. Thus, the fan blade is not only a working component but also a supporting and connection component for the rim and the wheel hub, forming a penetrating-through compressor and turbine with no air leakage in a radical direction and no resistance in an axial direction. The working efficiency is thus significantly improved. Secondly, the front part of the first wheel-shaped fan of the compressor (indicated as 11 in
The driving component comprises a plurality of driving axle sleeves, wherein each of the wheel-shaped fans of the turbine drives a corresponding wheel-shaped fan of the compressor to rotate, and each of the driving axle sleeves is provided between the wheel-shaped fan of the turbine and the wheel-shaped fan of the compressor (the wheel-shaped fan of the turbine 45 is corresponding to the main wheel-shaped fan 15 and the auxiliary wheel-shaped fan 25 of the compressor, with the driving axle sleeve 35 connecting between the three, in
The axle sleeves (indicated as 31, 32, 33, 34, 35, 36, 37, 38 and 39 in
A plurality of penetrating holes are provided on a wall of each of the axle sleeves.
A guiding cone (indicated as 30 in
A plurality of circular keys or key grooves (indicated as Xe in
A plurality of driving keys or key groove rings (indicated as Xg in
The rolling ratchet (indicated as Xk in
Beneficial effects of the driving axle sleeve of the driving component in present disclosure are as follows compared to the prior art. Firstly, spaces are left between the axle sleeves so that no interactive effect exists during their rotation. Penetrating-through holes are provided on the wall of the axle sleeves. A guiding cone is provided in the central driving axle sleeve, guiding the air and dissipating heat. Secondly, the driving axle sleeves are respectively suspended on the wheel hubs of the wheel-shaped fans of the compressor and on the wheel hubs of the wheel-shaped fans of the turbine. The engine penetrates through axially, without any components for fixedly supporting the driving axle sleeves such as bearings and holders. Thus the working efficiency of the turbine and the compressor are enhanced.
The structural and installed component comprises a plurality of supporting disks, a plurality of disk-fixing bolts, a plurality of assembling bolt sets, a middle casing and a circular combustor.
Wherein each of the supporting disks is a round shaped disk component where a plurality of ball bearings and a slide way support each of the wheel-shaped fans of the compressor and the turbine to rotate.
The supporting disks comprise a plurality of supporting disks (indicated as 61, 62, 63, 64, 65, 66, 67, 68 and 69 in
Wherein, the ball bearings and the slide way (indicated as Xd in
A plurality of disk-fixing holes (indicated as Xn in
The disk-fixing bolts (indicated as 71 in
A plurality of assembling holes (indicated as Xm in
A plurality of assembling bolt sets (indicated as 72 in
The circular combustor (indicated as 73 in
The starting component and parts comprises a starting motor and a starting gear train.
Wherein the starting motor (indicated as 81 in
The starting gear train (indicated as 82 in
Reference numerals for the components and parts mentioned above are shown as follows.
Additionally, reference numerals for functional components mentioned above are shown as follows. In general, the functional components are indicated as Xy, wherein X stands for a component, and y stands for a functional part of the component.
In order to illustrate clearly improvements of the technical solutions on the working and driving mode, the structure, the cooling mode as well as the starting mode, embodiments are given below in details. So that the above features and advantages of the present disclosure are readily understood.
In the multiple axle-sleeve driving bidirectional rotating wheel-shaped fan turbine and a bushing wheel-shaped fan compressor, one wheel-shaped fan of the turbine drives the corresponding wheel-shaped fan of the compressor to rotate by the corresponding driving axle sleeve.
The wheel-shaped fan of the turbine, the corresponding wheel-shaped fan of the compressor and the corresponding driving axle sleeve form a group. A rotating speed and a rotating direction within the group are the same. The rotating direction of the group is opposite to a rotating direction of an adjacent group. The rotating speed (absolute value) of the group is different to a rotating speed of the adjacent group. Except for the first wheel-shaped fan (indicated as 11 in
Beneficial effects of the working and driving mode in present disclosure are as follows compared to the prior art. Firstly, two wheel-shaped fans of every working stage with bidirectional rotating (forward and opposite) has a relative rotation speed more than twice of each stage fan blades (a rotor fan blade and a stator fan blade) of the existing compressor of the engine. Thus the working efficiency is improved and a stage number decreases of wheel-shaped fan of the compressor and the turbine. Secondly, a positive torque counteracts a negative torque, which are formed by wheel-shaped fans with bidirectional rotation, imposing a small effect on the external framework and beneficial to enhancing the structure and reducing the weight. Thirdly, the rotating speed of the wheel-shaped fan is increased by increasing a number of the working stages, since the independency that one wheel-shaped fan of the turbine drives one wheel-shaped fan of the compressor through one driving axle sleeve. If some wheel-shaped fan stall due to a resistance of the air inflow, the other wheel-shape fans work normally, thereby avoiding occurrence of engine surge. Fourthly, when an airplane starts to fly or flies with a low speed, the working efficiency is enhanced when the main wheel-shaped fans drive the auxiliary wheel-shaped fans and the fan blades unfold to form a wide chord fan blade (
The structure of the multiple axle-sleeve driving bidirectional rotating wheel-shaped fan turbine and a bushing wheel-shaped fan compressor is as follows. An external casing of the circular combustor and the middle casing form a middle double-sleeve structure. A circular funnel shaped external framework with a lattice structure (shown in
Beneficial effects of the structure in present disclosure are as follows compared to the prior art. Firstly, a structure rigidity is excellent with a light weight, as the entire body of the engine comprises the middle double-sleeve structure and the external framework with a cell structure at two ends. This structure facilitates ventilation and heat dissipation of external body of the engine. Secondly, the driving axle sleeves only transmit torque and bear a small part of bending moment of gravity. The driving axle sleeves is made from thin material, and a plurality of axle sleeves sleeved together with space between each other. The driving sleeve is respectively suspended on the top of the wheel hub of the corresponding wheel-shaped fan of the compressor and the turbine. There is no impact between each other and no bearings or other components or parts are necessary. Ventilation and heat dissipation are excellent.
The cooling mode of the multiple axle-sleeve driving bidirectional rotating wheel-shaped fan turbine and a bushing wheel-shaped fan compressor is as follows. Cold air enters into the central driving axle sleeve (indicated as 31 in
Beneficial effects of the structure in present disclosure are as follows compared to the prior art. Firstly, the cool air flows through the rims of the wheel-shaped fans of the compressor, and the space between the driving axle sleeves, the central area of the circular combustor as well as the hollow fan blade of the wheel-shaped fan of the turbine with a high speed from outside to inside, from the front to the end to take away the heat, thereby increasing heat-resistant quality of the components and parts of the engine and creating favourable condition for increasing the compression ratio of the compressor and the working temperature of the turbine. Secondly, a high negative pressure area is formed at the rear end of the central driving axle sleeves since a wake flow of hot air ejected by the turbine is supersonic. This wake flow provides a free power to the cooling mode of the air flow. The structure is simple and the cooling effect is excellent.
The starting mode of the multiple axle-sleeve driving bidirectional rotating wheel-shaped fan turbine and a bushing wheel-shaped fan compressor is as follows. The starting motor (indicated as 81 in
Beneficial effects are as follows of the structure in present disclosure compared to the prior art. Firstly, energy consumption is small during the starting process. Secondly, the starting components and parts are simple.
The embodiments described above are only the description of preferred embodiments of the present invention, but not limitation of the scope of the present invention. Any changes or improvement made by people having ordinary skill in the art within spirit of the present invention shall be included in the protection scope of the present invention.
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| 3385509 | Garnier | May 1968 | A |
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| 3937592 | Bammert | Feb 1976 | A |
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| 20150240836 | Guemmer | Aug 2015 | A1 |
| Number | Date | Country |
|---|---|---|
| 1487180 | Jul 2002 | CN |
| 103562518 | May 2011 | CN |
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| Number | Date | Country | |
|---|---|---|---|
| 20180142619 A1 | May 2018 | US |
| Number | Date | Country | |
|---|---|---|---|
| Parent | PCT/CN2015/000635 | Sep 2015 | US |
| Child | 15849640 | US |
