Integrated vortex core of secondary vortex culvert engine

Abstract

The integrated vortex core of the secondary turboculvert engine comprises an air pressing channel shell in running fit with an outer conical shell, an annular inner cavity arranged around the center line of the air pressing channel shell is formed in the air pressing channel shell, and the front end and the rear end of the air pressing channel shell are provided with an air suction opening and an air jet opening which are communicated with the annular inner cavity respectively. The area of the cross section of the annular inner cavity is gradually reduced in the airflow direction; the air pressing channel shell is further connected with a multi-curvature special-shaped fan blade located in the annular inner cavity, and the multi-curvature special-shaped fan blade comprises a spiral section, a straight plate section and an inclined section which are sequentially connected in the air flow direction. According to the integrated turbine core of the secondary turboculvert engine, the air passage resistance is small, and the energy conversion efficiency is high.

Description

Technical Field

[0001] This invention relates to the field of secondary turbofan-driven electric engines, and more particularly to an integrated turbofan core of a secondary turbofan-driven electric engine, wherein the secondary turbofan-driven electric engine is an electrically driven secondary turbofan-driven pressurized jet propulsion device, mainly used in electrically driven small and medium-sized aircraft. Background Technology

[0002] Our company's previously developed "Secondary Vortex-Guided Electric Drive Engine" (publication number CN116002057A) has undergone small-scale and pilot-scale testing, verifying the feasibility of its technical principles. The vortex core of the "Secondary Vortex-Guided Electric Drive Engine" is constrained by its separate multi-stage pressurized fan blades and secondary fan blade structure, making it difficult to further reduce airflow resistance during operation. Through repeated simulations and experiments, and continuous improvements, we have invented an "integrated vortex core" that is superior to the original separate multi-stage pressurized fan blades plus secondary fan blades. Summary of the Invention

[0003] The purpose of this invention is to provide an integrated turbine core for a secondary vortex-guided engine, which has low airflow resistance and high energy conversion efficiency.

[0004] To achieve the above objectives, the present invention provides an integrated turbine core for a secondary vortex-driven engine, comprising a compressor housing that rotates with an outer conical shell, an annular cavity arranged around its centerline within the compressor housing, an air intake and an exhaust port communicating with the annular cavity at the front and rear ends of the compressor housing, respectively, and the cross-sectional area of ​​the annular cavity gradually decreases along the airflow direction; the compressor housing is also connected to a multi-curvature irregular fan blade located in the annular cavity, the multi-curvature irregular fan blade comprising a spiral section, a straight section, and an inclined section connected sequentially along the airflow direction.

[0005] Furthermore, the spiral segment is arranged around the axis of the annular inner cavity, and the angle between the projection of the front edge and the rear edge of the spiral segment along the axial direction of the annular inner cavity is the blade extension angle A, which is 20°-360°.

[0006] Furthermore, the slope of the spiral segment relative to the axial direction of the annular inner cavity is the blade slope i3, and the blade slope i3 is 10%-100%.

[0007] Furthermore, the straight plate segment and the axial direction of the annular inner cavity are located in the same plane.

[0008] Furthermore, the angle between the inclined section's plate surface and the axis of the annular inner cavity is a back-spray chamfer B, which is 30-60°.

[0009] Furthermore, the compressor housing includes a relatively fixed compressor outer shell and a compressor inner shell, with the compressor outer shell located outside the compressor inner shell, forming the annular inner cavity between the two; the compressor housing is connected to a rotating shaft arranged coaxially with it.

[0010] Furthermore, the slope of the outer wall of the annular inner cavity relative to the axis of the annular inner cavity is the outer slope i2 of the air duct, and the slope of the inner wall of the annular inner cavity relative to the axis of the annular inner cavity is the inner slope i1 of the air duct. The outer slope i2 of the air duct is 1%-8%, and the inner slope i1 of the air duct is 10%-20%.

[0011] Furthermore, the front end of the inner shell of the compressor duct is connected to a central fairing, and the rotating shaft is connected to the inner shell of the compressor duct through structural ribs.

[0012] Beneficial effects

[0013] Compared with the prior art, the integrated turbine core of the secondary vortex-guided engine of the present invention has the following advantages:

[0014] 1. Compared with the split multi-stage pressurized fan blades and secondary fan blades used in the "secondary vortex electric drive engine", the integrated vortex core in this scheme has significantly reduced air passage resistance by about 15% and higher energy conversion efficiency.

[0015] 2. The entire vortex core is manufactured as a single piece, eliminating all connection points and improving product quality and cost-effectiveness.

[0016] 3. The multi-curved irregular fan blades consist of a spiral section, a straight section, and an inclined section connected sequentially along the airflow direction. While having a simple structure, it can provide mechanical propulsion and pressure to the air throughout the entire air duct. Among them, the spiral section has a blade extension angle A of 20°-360°, and the expansion of the blade extension angle A is equivalent to a multi-stage pressurization effect.

[0017] 4. Traditional turbofan engines have a venting gap problem because the fan blades need to rotate relative to the outer vortex casing, leaving a gap between the outer edge of the fan blade and the inner wall of the outer vortex casing. However, the integrated turbofan core of this solution has multi-curved irregularly shaped fan blades that are relatively fixed to the compressor duct shell, eliminating the outer vortex casing and thus the venting gap problem. The compressor duct shell eliminates the air back pressure gap between the turbofan core and the engine casing, thus significantly increasing the upper limit of turbofan core compression. For example, the original turbofan core's airflow compression ratio at an engine energy conversion rate of over 70% is difficult to exceed 6 times, while with the integrated turbofan core of this solution, the airflow compression ratio at an engine energy conversion rate of over 70% can reach 10 times. Here, the airflow compression ratio refers to the ratio of the airflow cross-sectional area of ​​the air intake and exhaust port, which can be understood as the airflow acceleration ratio.

[0018] The invention will become clearer from the following description, taken in conjunction with the accompanying drawings, which are used to explain embodiments of the invention. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 A front view of the integrated turbine core of the secondary vortex-driven engine;

[0021] Figure 2 Left view of the integrated turbine core of the secondary vortex-driven engine;

[0022] Figure 3 for Figure 1 CC view (excluding multi-curvature irregular fan blades);

[0023] Figure 4 This is a partial assembly cross-sectional view of the integrated turbine core of the secondary vortex blower engine and the outer cone shell of the engine.

[0024] Figure 5 A top view of a multi-curved, irregularly shaped fan blade;

[0025] Figure 6 This is a schematic diagram showing the main dimensions of the compressor housing;

[0026] Figure 7 A schematic diagram showing the main dimensions of a multi-curved irregular fan blade;

[0027] Figure 8 for Figure 7 The D-direction view;

[0028] Figure 9 One of the schematic diagrams showing the gas flow direction of the integrated vortex core of a secondary vortex-driven engine;

[0029] Figure 10 This is the second schematic diagram of the gas flow direction in the integrated turbine core of a secondary vortex-driven engine. Detailed Implementation

[0030] Embodiments of the present invention will now be described with reference to the accompanying drawings.

[0031] Example

[0032] Specific embodiments of the present invention are as follows: Figures 1 to 10As shown, an integrated turbine core of a secondary vortex-guided engine includes a compressor housing 1 that rotatably engages with the engine's outer conical shell 8. The compressor housing 1 has an annular inner cavity 6 arranged around its centerline. The front and rear ends of the compressor housing 1 are respectively provided with an air intake 3 and an exhaust port 4 communicating with the annular inner cavity 6. The cross-sectional area of ​​the annular inner cavity 6 gradually decreases along the airflow direction. The compressor housing 1 is also connected to a multi-curvature irregular fan blade 5 located within the annular inner cavity 6. The multi-curvature irregular fan blade 5 includes a helical section 51, a straight section 52, and an inclined section 53 connected sequentially along the airflow direction.

[0033] In this embodiment, there are 10 multi-curvature irregular fan blades 5, which are evenly distributed around the axis of the annular inner cavity 6.

[0034] The helical segment 51 is arranged around the axis of the annular inner cavity 6. The angle between the projections of the front and rear edges of the helical segment 51 along the axial direction of the annular inner cavity 6 is the blade extension angle A, which ranges from 20° to 360°. In this embodiment, the blade extension angle A is 90°. The blade extension angle A is a core parameter for controlling the applied pressure.

[0035] The slope of the spiral section 51 relative to the axis of the annular inner cavity 6 is the blade slope i3, which is the core parameter for controlling pressure and flow velocity. The blade slope i3 is 10%-100%, and the value of the blade slope i3 at various points of the spiral section 51 gradually increases along the flow direction of the airflow.

[0036] The straight plate section 52 and the annular inner cavity 6 are located in the same plane along their axes.

[0037] The angle between the plate surface of the inclined section 53 and the axis of the annular inner cavity 6 is the reverse jet chamfer B, which is a core parameter for recovering the vortex force of the airflow. The reverse jet chamfer B is 30-60°. In this embodiment, the reverse jet chamfer B is 45°.

[0038] The compressor housing 1 includes a relatively fixed compressor outer shell 11 and a compressor inner shell 12. The compressor outer shell 11 is located outside the compressor inner shell 12, forming an annular inner cavity 6 between them. The compressor housing 1 is connected to a rotating shaft 2 arranged coaxially with it. The front end of the compressor inner shell 12 is connected to a central fairing 13, and the rotating shaft 2 is connected to the compressor inner shell 12 through a structural rib 14.

[0039] The integrated turbine core of this secondary vortex-driven engine is mainly manufactured as a single unit, consisting of a rotating shaft 2, a compressor duct outer shell 11, a compressor duct inner shell 12, and multi-curvature irregular fan blades 5, forming multiple integrated fluid pressurization and acceleration channels composed of the outer shell, inner shell, and multi-curvature irregular fan blades 5.

[0040] The inner diameter of the front end of the compressor casing 11 is the inlet diameter D1, and the maximum diameter of the central fairing 13 is the shroud diameter D2. The shroud diameter D2 is generally 0.2-0.3 times the inlet diameter D1, and involves many parameters such as flow rate, air resistance, and volume. There will be an optimal value for a fixed model.

[0041] The length of the compressor housing 11 is the duct length L, which is a parameter closely related to the engine's maximum boost pressure and duct resistance. The inlet diameter D1 is 0.6-0.8 times the duct length L and is a core parameter for engine thrust.

[0042] The slope of the outer wall of the annular inner cavity 6 (i.e., the inner wall of the compressed air duct shell 11) relative to the axis of the annular inner cavity 6 is called the outer slope i2 of the air duct. This is an important parameter for controlling air resistance. The value of the outer slope i2 ranges from 1% to 8%. The smaller the value, the lower the resistance, but the longer the air duct length L will be. The slope of the inner wall of the annular inner cavity 6 relative to the axis of the annular inner cavity 6 is called the inner slope i1 of the air duct. This is also an important parameter for controlling air resistance. The value of the inner slope i1 ranges from 10% to 20%. The smaller the value, the lower the resistance, but the longer the air duct length L will also be.

[0043] The above parameters will affect each other during the design process. For a specific model design, the goal is to find the optimal combination of these parameters under the specific requirements.

[0044] An annular boss 7 is provided on the outer wall of the compressor housing 1, and an annular anti-seepage semi-circular groove 71 is provided on the rear end face of the annular boss 7. The rear end face of the annular boss 7 is adapted to the stepped limiting part 81 on the inner wall of the outer conical shell 8. A sealing ring can be embedded in the anti-seepage semi-circular groove 71, and the sealing ring contacts the stepped limiting part 81 of the outer conical shell 8. The anti-seepage semi-circular groove 71 can ensure the pressure of the vortex cavity and also act as a bearing.

[0045] One end of the rotating shaft 2 is linked to the drive unit, for example, it can be connected to the power end of an engine. A tensile boss 21 is provided on the outer wall of the rotating shaft 2 near one end. A bearing 20 is fitted onto one side of the tensile boss 21, and the rotating shaft 2 rotates in conjunction with the outer cone housing 8 of the engine via the bearing 20. During operation, the drive unit drives the integrated turbine core of the secondary turbofan engine to rotate relative to the outer cone housing 8 via the rotating shaft 2. Figure 9 , Figure 10 As shown, when the turbine core rotates under mechanical force, gas enters through the air intake 3, passes through the integrated fluid channel, and flows out from the jet nozzle 4. This process converts mechanical energy into air energy and ultimately becomes the thrust of the engine.

[0046] The present invention has been described above in conjunction with the preferred embodiments, but the present invention is not limited to the embodiments disclosed above, but should cover various modifications and equivalent combinations made in accordance with the essence of the present invention.

Claims

1. An integrated turbine core for a secondary vortex-guided engine, characterized in that, The compressor housing (1) is rotatably fitted with the outer cone shell (8). The compressor housing (1) has an annular inner cavity (6) arranged around its center line. The front and rear ends of the compressor housing (1) are respectively provided with an air intake (3) and an air jet (4) connected to the annular inner cavity (6). The cross-sectional area of ​​the annular inner cavity (6) gradually decreases along the airflow direction. The compressor housing (1) is also connected to a multi-curvature irregular fan blade (5) located in the annular inner cavity (6). The multi-curvature irregular fan blade (5) includes a spiral section (51), a straight plate section (52), and an inclined section (53) connected in sequence along the airflow direction.

2. The integrated turbine core of a secondary vortex-guided engine according to claim 1, characterized in that, The spiral segment (51) is arranged around the axis of the annular inner cavity (6). The angle between the projection of the front edge and the rear edge of the spiral segment (51) along the axial direction of the annular inner cavity (6) is the blade extension angle A, which is 20°-360°.

3. The integrated turbine core of a secondary turbofan engine according to claim 1, characterized in that, The slope of the spiral segment (51) relative to the axis of the annular inner cavity (6) is the blade slope i3, which is 10%-100%.

4. The integrated turbine core of a secondary vortex-guided engine according to claim 1, characterized in that, The straight plate segment (52) and the annular inner cavity (6) are located on the same plane.

5. The integrated turbine core of a secondary turbofan engine according to claim 1, characterized in that, The angle between the plate surface of the inclined section (53) and the axis of the annular inner cavity (6) is the back spray chamfer B, which is 30-60°.

6. The integrated turbine core of a secondary vortex-guided engine according to claim 1, characterized in that, The compressed air duct housing (1) includes a relatively fixed compressed air duct outer shell (11) and a compressed air duct inner shell (12). The compressed air duct outer shell (11) is located outside the compressed air duct inner shell (12), and the two form the annular inner cavity (6). The compressed air duct housing (1) is connected to a rotating shaft (2) arranged coaxially with it.

7. An integrated turbine core for a secondary turbofan engine according to claim 1 or 6, characterized in that, The slope of the outer wall of the annular inner cavity (6) relative to the axis of the annular inner cavity (6) is the outer slope i2 of the air duct, and the slope of the inner wall of the annular inner cavity (6) relative to the axis of the annular inner cavity (6) is the inner slope i1 of the air duct. The outer slope i2 of the air duct is 1%-8%, and the inner slope i1 of the air duct is 10%-20%.

8. The integrated turbine core of a secondary vortex-guided engine according to claim 6, characterized in that, The front end of the inner shell of the compressed air duct (12) is connected to a central fairing (13), and the rotating shaft (2) is connected to the inner shell of the compressed air duct (12) through a structural rib (14).

9. An integrated turbine core for a secondary turbofan engine according to claim 1 or 6, characterized in that, The outer wall of the compressed air passage housing (1) is provided with an annular boss (7), and the rear end face of the annular boss (7) is provided with an annular anti-seepage semi-circular groove (71); the rear end face of the annular boss (7) is adapted to the stepped limiting part (81) on the inner wall of the outer conical shell (8).

Images