Open type rotor engine
By designing an automatic gas induced structure and a trail controller in an open rotor engine, the problem of difficulty in reducing the blade noise of the open rotor engine in the prior art is solved, and effective noise control and aerodynamic performance optimization are achieved.
Patent Information
- Application Number
- CN202311610134.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-11-28
- Publication Date
- 2025-05-30
AI Technical Summary
Existing open-rotor engines have challenges in reducing blade noise, especially because traditional noise reduction measures are difficult to effectively solve due to their complex flow and noise mechanisms.
By designing an automatic air-induced structure, it includes setting up a plurality of oblique micro-holes near the nose cone to guide the far field to flow into the internal air flow channel, and setting up multiple blowing outlets at the leading edge of the static blade, the air flow channel is used to guide the vortexes such as the blade tip vortex formed in the trailing edge area of the front rotor blade tip to the blowing outlet, thereby reducing the interference noise of the front and rear blades.
The blade noise of the open rotor engine is effectively reduced. By adjusting the blade load and arranging the trail controller, the aerodynamic performance and noise regulation are achieved, and the blade self-noise and interference noise are significantly reduced.
Smart Images
Figure CN120062160A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to an open rotor engine, and specifically to reducing the blade noise of an open rotor engine. The present invention belongs to the field of engine design. Background Art
[0002] Due to the current global continuous attention to the issue of "energy conservation and emission reduction", "green power" has become the future development trend of the aviation industry. The open rotor engine combines the characteristics of low fuel consumption rate of the turboprop engine and suitability for high-speed flight of the turbofan engine. Compared with the conventional turbofan engine of the same thrust level, the fuel consumption rate and CO2 emissions of the open rotor engine can be reduced by 20% - 30%. The open rotor engine has the advantages of high propulsion efficiency, low fuel consumption rate, and low pollutant emissions, and has become a typical representative of the environmentally friendly aeroengine.
[0003] Compared with the turbofan engine, noise reduction can be achieved by laying acoustic linings on the intake duct and bypass duct walls. Since the open fan has no casing enclosure, the noise problem is prominent and is a difficult problem to overcome. The future strict airworthiness noise requirements will become a condition restricting the introduction of open fan engine products.
[0004] Since it adopts the form of two rows of counter-rotating rotors, the flow and noise mechanisms are very complex; the noise of the open rotor engine comes from multiple aspects, such as the thickness of the blades, whether the tip speed is faster than the speed of sound, etc.
[0005] The open fan noise is the main noise source of the open fan engine. This noise includes the tip vortex interference tone of the blade, the viscous wake interference tone, the interference tone of the potential fields of the front and rear rows of blades, and the single rotor blade tone, etc., and involves the tip vortex interference effect, the interference effect of the viscous wake of the front rotor on the rear rotor, and the interference effect of the viscous wake of the pylon on the rotor, etc.
[0006] For the open fan without a bypass duct, its noise cannot be suppressed by using noise reduction linings like the traditional turbofan engine anymore. It can only be improved by controlling the noise source through aerodynamic acoustic design on the premise of not affecting the aerodynamic performance.
[0007] In terms of noise reduction of the open rotor engine, a large amount of research work has been done at home and abroad, and a series of noise reduction measures have been developed. Noise control is carried out in the source design to reduce the intensity of the blade pulsating force or weaken their acoustic influence.
[0008] In order to effectively reduce the noise of the open rotor fan, there is still a need to further improve the structure of the existing open rotor engine. Summary of the Invention
[0009] Aiming at the above problems of the prior art, the purpose of the present invention is to provide an open rotor engine that can effectively reduce the noise of the open rotor fan.
[0010] In a first example of the open rotor engine, the open rotor engine includes: an air flow inlet disposed in a housing of a nose cone portion of the open rotor engine, facing the heading direction of the open rotor engine; a first air flow passage disposed within the open rotor engine; a plurality of blowing outlets disposed at leading edges of stator blades in a rear row of the open rotor engine and spaced from a blade root to a blade tip of the stator blades, facing the heading direction of the open rotor engine; a second air flow passage disposed within the stator blades; and wherein the air flow inlet is in fluid communication with the plurality of blowing outlets via the first air flow passage and the second air flow passage.
[0011] In a second example of the open rotor engine, optionally including the first example, one of the plurality of second air flow passages corresponds to one or two or more of the plurality of blowing outlets, and the first air flow passage has a dividing section at a connection with the second air flow passage for dividing an incoming air flow into the plurality of second air flow passages.
[0012] In a third example of the open rotor engine, optionally including one or more of the first example and the second example, an internal passage for surrounding and fixing the plurality of second air flow passages is provided in stator blades in a rear row of the open rotor engine.
[0013] In a fourth example of the open rotor engine, optionally including one or more of the first example to the third example, the air flow inlet has a plurality of micro holes on an outer contour surface of a housing of a nose cone portion of the open rotor engine.
[0014] In a fifth example of the open rotor engine, optionally including one or more of the first example to the fourth example, the air flow inlet has a diversion passage penetrating the housing, and the plurality of micro holes are all in communication with the diversion passage, wherein the diversion passage is smooth and curved and curved in a direction of an oncoming air flow along an outer contour surface of the housing.
[0015] In a sixth example of the open rotor engine, optionally including one or more of the first example to the fifth example, the first air flow passage has a transition section at a connection with the air flow inlet, and the diversion passage is in fluid communication with the transition section, wherein the transition section is of a gradually expanding type.
[0016] In a seventh example of the open rotor engine, optionally including one or more of the first example to the sixth example, the rotor blades in a front row of the open rotor engine are designed such that a blade camber from a blade tip to a blade root varies from 105% to 130%, so that the blade camber increases in a direction from the blade tip to the blade root.
[0017] In the eighth example of the open rotor engine, optionally including one or more of the first to seventh examples, the rotor blades in the front row and the stator blades in the rear row of the open rotor engine are designed such that the airfoil thickness varies from 50% to 150% of the initial thickness from the blade tip to the blade root, so that the airfoil thickness increases in the direction from the blade tip to the blade root.
[0018] In the ninth example of the open rotor engine, optionally including one or more of the first to eighth examples, a plurality of first wake controllers are provided at intervals from the blade tip to the blade root at the trailing edge of the rotor blades in the front row of the open rotor engine.
[0019] In the tenth example of the open rotor engine, optionally including one or more of the first to ninth examples, a plurality of second wake controllers are provided at intervals from the blade tip to the blade root at the trailing edge of the stator blades in the rear row of the open rotor engine.
[0020] The present invention realizes blade noise reduction through an automatic air extraction structure. A large number of inclined micro-holes are designed on the outer surface of the hub near the nose cone, which can make the oncoming flow from far field smoothly enter the internal air flow channel, and at the same time the micro-holes on the surface can reduce the influence on the air flow; a plurality of air flow channels are designed inside the rear row of stators, so that the leading edge of the stator blades automatically extracts air and blows air, dispersing the tip vortex formed at the trailing edge of the tip of the front row of rotor blades, the shed vortex shed from the trailing edge of the blade, the root vortex formed at the hub outlet, and the wake of the front row of rotors, reducing the intensity of the wake of the front row of rotors hitting the rear row of blades, so as to reduce the interference noise between the front and rear rows of blades.
[0021] The present invention reduces noise by adjusting blade loading. Adjusting the aerodynamic load from the blade tip to the blade root can reduce the aerodynamic load at the blade tip and suppress the main noise source. At the same time, the regulation of aerodynamic performance and noise is realized. The aerodynamic load at the blade tip is reduced, and the blade self-noise as the main sound source is reduced.
[0022] The present invention attenuates the sound source intensity and weakens the interference of the wakes between the front and rear rows by arranging wake controllers. A row of wake controllers with an airfoil streamline shape is designed at the trailing edge of the suction surface of the blade. The wake controller is designed with a channel that is narrow in the front and wide in the rear, controlling the direction of the blade wake and smoothing the flow field, suppressing the formation of wake vortices, and reducing the blade self-noise. The intensity of the wake of the front row of rotors hitting the rear row of blades is reduced, and the interference noise between the front and rear rows of blades is reduced.
[0023] In summary, through various active and passive measures proposed in this design, the noise of the open rotor blades can be effectively reduced. Brief Description of the Drawings
[0024] To describe embodiments of the above and other features of the present invention, a more specific description of the present invention briefly described above will be presented with reference to the exemplary embodiments of the present invention shown in the accompanying drawings. It is understood that these drawings depict only exemplary embodiments of the present invention and should not be considered as limiting its scope. The present invention will be described and explained by using the drawings and additional features and details. In the drawings:
[0025] Figure 1 is a schematic side view of an air flow passage of an open rotor engine according to an embodiment of the present invention;
[0026] Figure 2 is Figure 1 a schematic side view at an air flow inlet of the open rotor engine of;
[0027] Figures 3a - 3c is a schematic perspective view of a rotor blade of an open rotor engine according to some embodiments of the present invention; and
[0028] Figure 4 is a schematic diagram of the camber of a rotor blade of an open rotor engine according to an embodiment of the present invention,
[0029] Figure 5 is a schematic diagram of the blade thickness of a rotor blade of an open rotor engine according to an embodiment of the present invention,
[0030] Figure 6 is a schematic side view of a wake controller of an open rotor engine according to an embodiment of the present invention; and
[0031] Figure 7 is Figure 6 a schematic perspective view of the wake controller of the open rotor engine of.
[0032] Figures 1 to 7 The dimensions in are only schematic and need not be drawn to scale, but are intended to illustrate more clearly. In other embodiments, other relative dimensions may be used.
[0033] Herein and throughout the following, the same features appearing in different drawings are denoted by the same or similar reference numerals.
[0034] List of reference numerals:
[0035] 1 Open rotor engine
[0036] 2 Housing 2
[0037] 2a Contour outer surface
[0038] 2b Contour outer inner surface
[0039] 10 Rotor blade
[0040] 20 stator vane
[0041] 21 internal passage
[0042] 30 air inlet
[0043] 31 micropore
[0044] 32 diversion passage
[0045] 40 air blowing outlet
[0046] 50 first air flow passage
[0047] 51 transition section
[0048] 52 splitting section
[0049] 60 second air flow passage
[0050] 70 first wake controller
[0051] 80 second wake controller Detailed implementation manners
[0052] First, the present invention mainly relates to the field of open rotor engines. In particular, the present invention relates to the processes related to the rotor blades in the front row and the stator blades in the rear row of an open rotor engine, but is not limited to the blades at these positions.
[0053] The term "heading direction" used herein is intended to describe the flight direction of an aircraft having an open rotor engine.
[0054] The terms "front row" and "rear row" used herein are intended to describe that the rotor blades of an open rotor engine are located in the front in the heading direction, and the stator blades are located in the rear in the heading direction. Therefore, there is a possibility that the air flow shed from the rotor blades impacts the stator blades.
[0055] The term "leading edge" used herein is intended to describe the blade portion of a blade at the front end in the blade rotation direction, and the term "trailing edge" is intended to describe the blade portion of a blade at the rear end in the blade rotation direction.
[0056] The term "extend" used herein is intended to describe that a component has a certain length in the extending direction from the starting position to the terminal position.
[0057] The term "thickness of the blade" used herein is intended to describe the width of the blade in the direction perpendicular to the heading direction in a cross-sectional plane parallel to the heading direction and perpendicular to the extending direction of the blade from the blade root to the blade tip.
[0058] The directional terms used in this document, such as "vertical", "horizontal", "top", "bottom", "upper", "lower", "inner", "inward", "outer", and "outward", are used to assist in describing the present invention according to the directions of the embodiments shown in the drawings. The directional terms are not absolute up, down, horizontal, vertical, etc., and should not be construed as limiting the present invention to any specific direction.
[0059] The terms "comprising", "having", "including" and their variants as used herein are intended to be open transitional phrases, terms or words that require the presence of the specified element / step and also permit the presence of other elements / steps.
[0060] In the present invention, unless expressly stated to the contrary, the terms "first", "second", etc. are not intended to denote any difference in order, position, quantity or importance, but are merely used as labels to distinguish different positions and components.
[0061] The terms "about" and "substantially" may be used to include any numerical value that can vary without changing the basic function of that value. Generally, the terms "about" and "substantially" may refer to plus or minus 10% of the indicated number. When used with a range, "about" and "substantially" also disclose the range defined by the absolute values of the two endpoints. For example, "about 2 to about 4" also discloses the range "from 2 to 4".
[0062] All ranges disclosed herein include the recited endpoints and can be combined independently (e.g., the range "from 2 to 4" includes the endpoints 2 and 4 and all intermediate values).
[0063] The numerical values used herein should be understood to include the same numerical values when rounded to the same number of significant digits, as well as numerical values that differ from the said numerical values by less than the experimental error of the numerical values determined by conventional measurement techniques of the type described in this application.
[0064] Finally, the numerical values given in the embodiments are only examples and not limitations on the scope of the present invention.
[0065] Automatic air - bleeding structure
[0066] In a non-limiting example, the open rotor engine 1 of the present invention may have rotor blades 10 in the front row and stator blades 20 in the rear row.
[0067] In a non-limiting example, the open rotor engine 1 of the present invention includes an automatic air bleeding structure, which mainly includes an air flow inlet 30, a blowing outlet 40, and an air flow channel that fluidly connects the two.
[0068] In one example, the air inlet 30 can be arranged in the housing 2 of the nose cone of the open rotor engine 1, and the air inlet 30 faces the heading direction of the open rotor engine 1 and serves as an inlet for receiving oncoming air flow.
[0069] The air flow enters the internal blowing channel through the air inlet 30 at the nose cone, and can automatically introduce the oncoming air flow into the internal duct for blowing the rear stator blades 20, which has the advantages of simple structure and no need for additional external power.
[0070] In one example, the open rotor engine 1 is provided with a plurality of blowing outlets 40 at the leading edge of the stator blades 20, which are spaced from the blade root to the blade tip along the span of the stator blades 20, and the blowing outlets 40 face the heading direction of the open rotor engine 1, allowing the air flow to blow out towards the front rotor blades 10.
[0071] The air flow blows out from the leading edge of the stator blades 20, and can disperse the tip vortices formed in the tip trailing edge region of the front rotor blades 10, the shedding vortices at the blade trailing edge, the root vortices formed at the hub, and the wakes of the front rotor blades, reducing the intensity of the wakes colliding with the rear stator blades 20, so as to reduce the interference noise between the front and rear blades.
[0072] In one example, the air inlet 30 is in fluid communication with the plurality of blowing outlets 40 via a first air flow channel 50 and a second air flow channel 60.
[0073] Among them, the first air flow channel 50 is an air flow channel arranged in the open rotor engine 1, with one end communicating with the air inlet 30 and the other end communicating with the second air flow channel 60.
[0074] Among them, the second air flow channel 60 is an air flow channel arranged in the stator blades 20, with one end communicating with the first air flow channel 50 and the other end communicating with the plurality of blowing outlets 40.
[0075] Adjust blade load
[0076] According to the aerodynamic theory, after the camber of a local area of the blade increases, the pressure difference between the suction surface and the pressure surface of this local area becomes larger, the work capacity of this local area is enhanced, and the aerodynamic load increases accordingly.
[0077] In a non-limiting example, the present invention designs the front rotor blades 10 of the open rotor engine 1 to have a blade root with large camber and large thickness through the control of the camber and thickness in the span direction, so as to increase the work capacity of the blade root and make the blade root area bear the vast majority of the blade aerodynamic load. The blade tip is designed as a thin airfoil with small camber and small thickness to reduce the aerodynamic load at the blade tip and reduce the blade self-noise.
[0078] The tip is the area that generates the most noise. By having the maximum camber at the root and a smaller camber at the tip, it is possible to allow the distribution of the surface load of the rotor blade 10 to be changed while keeping the overall total load of the blade constant and ensuring that the aerodynamic thrust of the blade remains unchanged. By design, part of the load at the tip is adjusted to other blade areas, such as the root area. At this time, the aerodynamic load of the rotor blade 10 moves downward towards the root center of gravity, reducing the aerodynamic load at the tip of the rotor blade 10, decreasing the noise level of the noise source, and attenuating the self-noise and interference noise of the rotor blade 10.
[0079] It can be understood that this improvement is not limited to the front-row rotor blades 10, but can also be applied to the rear-row stator blades 20.
[0080] In addition, through the spanwise control of the camber and thickness of the airfoil, the camber and airfoil thickness increase uniformly along the span from the tip to the root, allowing the reduction of the interference noise between the front and rear rows of blades. Moving the aerodynamic load from the tip to the root reduces the tip vortex and the wake intensity in the tip region. The present invention only changes the airfoil camber and airfoil thickness to achieve the reduction of blade noise and interference noise.
[0081] Wake controller
[0082] In a non-limiting example, the present invention arranges wake controllers at multiple locations on the blade, attenuating the sound source intensity and weakening the wake intensity.
[0083] The wake controller can include a channel that is narrower at the front and wider at the rear, causing the wake airflow to decelerate after passing through the wake controller, which can reduce the wake velocity.
[0084] The present invention designs the wake controllers 70 and 80 along the spanwise direction of the suction surface of the rotor blade 10 and the stator blade 20 to control the airflow in the direction from the root to the tip under the action of centrifugal force during high-speed rotation. It can effectively adjust the local flow fields at the root and the tip. After smoothing the flow field, the degree of flow field disorder at that place is reduced, and the formation of the tip vortex and the root vortex is suppressed, achieving the purpose of controlling the noise source and reducing the self-noise of the blade. Here, the second wake controller 80 can be the same as or recognized as the first wake controller 70 as long as it can meet the above purposes.
[0085] In addition, the wake controller 70 on the rotor blade 10 can smooth the wake flow field, forcefully change the movement trajectory of the wake, break the wake into smaller airflow clusters, reduce the intensity of the wake of the front-row rotor blade 10 colliding with the rear-row stator blade 20, and reduce the interference noise between the front and rear rows of blades.
[0086] The present invention will be further described below in conjunction with specific embodiments and the accompanying drawings. More details are set forth in the following description to facilitate a full understanding of the present invention. However, the present invention is clearly capable of being implemented in many other ways different from this description. Those skilled in the art can make similar generalizations and deductions according to the actual application situation without departing from the connotation of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.
[0087] Figure 1 A side view schematically showing the air flow passage of the open rotor engine 1 is shown.
[0088] In this embodiment, the open rotor engine has a plurality of second air flow passages 60, and one of the plurality of second air flow passages 60 corresponds to one or two of the plurality of blowing outlets 40.
[0089] The first air flow passage 50 has a diversion section 52 at the connection with the second air flow passage 60. The incoming air flow is diverted into a plurality of second air flow passages 60 with smaller diameters in the diversion section 52 of the first air flow passage 50.
[0090] In the diversion section 52 of the first air flow passage 50, when there is a diversion pipeline, the upstream has a higher air pressure than the downstream. Here, the upstream refers to the upstream in the flow direction of the air flow in the first air flow passage 50. Therefore, it is preferably designed that every two blowing outlets 40 near the root of the stator blade 20 share a second air flow passage 60 near the upstream.
[0091] It can be understood that the arrangement of the second air flow passage 60 and the blowing outlet 40 is not limited to this. Instead, it is also possible that only one second air flow passage 60 corresponds to all the blowing outlets 40, or each second air flow passage 60 corresponds to three or more blowing outlets 40, or each second air flow passage 60 corresponds to one blowing outlet 40, that is, having a separate blowing function, and each second air flow passage 60 blows separately.
[0092] In addition, when there are a plurality of second air flow passages 60 in the rear row of stator blades 20, in order to surround and fix the plurality of second air flow passages 60, the stator blade 20 may have an internal passage 21 and corresponding fixing components.
[0093] Figure 2 A side view schematically showing the air inlet 30 of the open rotor engine 1 is shown.
[0094] In this embodiment, the air inlet 30 has a plurality of micropores 31 on the outer contour surface 2a of the housing 2 of the nose cone portion of the open rotor engine 1. The micropores 31 of the air inlet 30 on the outer surface 2a of the hub of the housing 2 can reduce the influence on the air flow, and a large number of micropores 31 can smoothly introduce the far-field incoming air flow near the nose cone portion into the air flow channel inside the housing 2.
[0095] The diameter of the micropores 31 of the air inlet 30 can be in the range of 1 mm - 5 mm, preferably in the range of 2 mm - 4 mm.
[0096] In this embodiment, the air inlet 30 has a diversion channel 32 penetrating through the housing 2, and a plurality of micropores 31 communicate with the diversion channel 32. The diversion channel 32 of the air inlet 30 is smooth and curved, and is curved in the direction of the incoming air flow along the outer contour surface 2a of the housing 2.
[0097] The first air flow channel 50 has a transition section 51 at the connection with the air inlet 30, and the diversion channel 32 is in fluid communication with the transition section 51, wherein the transition section 51 is of a gradually expanding type, and smoothly introduces the air inlet 30 with a smaller diameter into the larger-sized first air flow channel 50.
[0098] Conventional air bleeding requires additional air bleeding devices and external energy input. In the present invention, by providing the air inlet 30 at the nose cone, designing the micropores 31, the curved diversion channel 32 and the gradually expanding transition section 51 in the air intake area of the air inlet 30 on the outer surface 2a of the hub of the housing 2, the far-field incoming air flow can smoothly enter the internal air flow channel to meet the leading edge blowing requirements of the rear stator blades.
[0099] Figures 3a - 3c A perspective view of the rotor blade 10 of the open rotor engine 1 of some embodiments is schematically shown. In Figures 3a - 3c this embodiment, the variations of the blade camber and thickness in the spanwise direction.
[0100] Figure 3a Compared with Figure 3b , the blade camber of the middle section of the rotor blade 10 is changed. Referring to Figure 4 , by changing θ 2 the blade camber of the blade cross-section can be changed. Among them, the camber line in the blade refers to the chord of the blade; θ 1 is the camber angle of the outer surface of the blade, characterizing the bending degree of the blade; θ 2 is the installation angle of the blade, reflecting the characteristic of the blade twist degree.
[0101] The rotor blade 10 has an airfoil design with an increasing airfoil camber from the blade tip to the blade root. In one example, the airfoil camber at the blade tip is 5 degrees, the airfoil camber at the mid-span is 20 degrees, and the airfoil camber at the blade root is 30 degrees( Figure 3a ). In other examples, the airfoil camber at the blade tip is 5 degrees, the airfoil camber at the mid-span is 20 degrees, and the airfoil camber at the blade root is 30 degrees( Figure 3b , 3c ).
[0102] Generally, the rotor blades 10 in the front row of the open rotor engine 1 are designed such that the airfoil camber varies from 105% to 130% from the blade tip to the blade root, so that the airfoil camber increases in the direction from the blade tip to the blade root.
[0103] Figure 3b Instead of Figure 3c changing the airfoil camber, the airfoil thickness distribution at the mid-section is changed. Referring to Figure 5 , there can be four control points on the suction side of the convex side of the blade, and the airfoil thickness distribution of the blade can be changed by moving the distance between the control points and the chord of the blade.
[0104] In addition, the rotor blade 10 has an airfoil design with an increasing airfoil normalized thickness (the ratio of thickness to chord length) from the blade tip to the blade root.
[0105] The rotor blades 10 in the front row and the stator blades 20 in the rear row of the open rotor engine 1 are designed such that the airfoil thickness varies from 50% to 150% of the initial thickness from the blade tip to the blade root, so that the airfoil thickness increases in the direction from the blade tip to the blade root.
[0106] Generally, from the blade tip to the blade root, preferably, the camber of the blade varies uniformly from 105% to 130% in the spanwise direction, the airfoil thickness varies uniformly from 50% to 150% of the initial thickness, and the airfoil normalized thickness (i.e., the ratio of thickness to chord length) varies uniformly from 105% to 130%. Here, the uniform variation means no convex or concave shape and a smooth transition.
[0107] Figure 6 A schematic side view of the wake controllers 70, 80 of the open rotor engine 1 is schematically shown. The rotor blades 10 in the front row of the open rotor engine 1 are provided with a plurality of first wake controllers 70 at the trailing edge spaced apart from the blade tip to the blade root, which can reduce the degree of turbulence in the airflow field. And preferably, the stator blades 20 in the rear row are provided with a plurality of second wake controllers 80 at the trailing edge spaced apart from the blade tip to the blade root.
[0108] Figure 7 A schematic perspective view of the wake controller of the open rotor engine which is Figure 6 is schematically shown.
[0109] Here, the second wake controller 80 may be the same as the first wake controller 70. These wake controllers are approximately 5 mm high and approximately 8 mm long in the flow direction, and are designed with an airfoil streamline shape to smooth the airflow at the blade wake.
[0110] Above, in order to make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention have been clearly and completely described in conjunction with the specific embodiments and the accompanying drawings of the present invention.
[0111] Although various embodiments have been described above, it should be understood that the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments, and they are presented by way of example rather than limitation. It is obvious to those skilled in the relevant art that the disclosed subject matter can be implemented in other specific forms without departing from its spirit and essential features.
[0112] In this process, various elements important to the present invention or elements conducive to the further development of the present invention will be mentioned in the content of specific examples. However, some of these elements can also be used for the further development of the present invention when separated from the content of the corresponding examples and other features of the corresponding examples. Therefore, the embodiments described above are considered to be exemplary rather than restrictive in all aspects and do not serve as a basis for any limitation to the present invention.
[0113] Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of the present invention to be protected. This disclosure also includes various variations and variations within the equivalent scope. In addition, various combinations, methods, further including only one element, other combinations, methods with more than one or less than one element also fall within the scope and thinking scope of this disclosure.
Claims
1. An open rotor engine, characterized in that, the open rotor engine (1) includes: an air inlet (30) which is arranged in a housing (2) of a nose cone portion of the open rotor engine (1) and faces the course direction of the open rotor engine (1); a first air flow channel (50) which is arranged inside the open rotor engine (1); a plurality of blowing outlets (40) which are arranged at leading edges of stator blades (20) in a rear row of the open rotor engine (1) and are spaced from a blade root to a blade tip of the stator blades (20) and face the course direction of the open rotor engine (1); and a second air flow channel (60) which is arranged inside the stator blades (20); wherein, the air inlet (30) is in fluid communication with the plurality of blowing outlets (40) via the first air flow channel (50) and the second air flow channel (60).
2. The open rotor engine according to claim 1, characterized in that, one of the plurality of second air flow channels (60) corresponds to one or two or more of the plurality of blowing outlets (40), and the first air flow channel (50) has a flow dividing section (52) at a connection with the second air flow channel (60) for dividing incoming air flow into the plurality of second air flow channels (60).
3. The open rotor engine according to claim 2, characterized in that, an internal channel (21) for surrounding and fixing the plurality of second air flow channels (60) is provided in stator blades (20) in a rear row of the open rotor engine (1).
4. The open rotor engine according to claim 1, characterized in that, the air inlet (30) has a plurality of micro holes (31) on an outer contour surface (2a) of the housing (2) of the nose cone portion of the open rotor engine (1).
5. The open rotor engine according to claim 4, characterized in that, the air inlet (30) has a diversion channel (32) penetrating through the housing (2), and the plurality of micro holes (31) are all in communication with the diversion channel (32), wherein the diversion channel (32) is smooth and curved and is curved in a direction of an oncoming air flow along the outer contour surface (2a) of the housing (2).
6. The open rotor engine according to claim 5, characterized in that, the first air flow channel (50) has a transition section (51) at a connection with the air inlet (30), and the diversion channel (32) is in fluid communication with the transition section (51), wherein the transition section (51) is of a gradually expanding type.
7. The open rotor engine according to claim 1, characterized in that, rotor blades (10) in a front row of the open rotor engine (1) are designed such that a camber from a blade tip to a blade root varies from 105% to 130%, so that the camber increases in a direction from the blade tip to the blade root.
8. The open rotor engine according to claim 1, characterized in that, the rotor blades (10) in the front row and the stator blades (20) in the rear row of the open rotor engine (1) are designed such that the airfoil thickness varies from 50% to 150% of the initial thickness from the blade tip to the blade root, so that the airfoil thickness increases in the direction from the blade tip to the blade root.
9. The open rotor engine according to claim 1, characterized in that, the rotor blades (10) in the front row of the open rotor engine (1) are provided with a plurality of first wake controllers (70) spaced apart from the blade tip to the blade root at the trailing edge.
10. The open rotor engine according to claim 9, characterized in that, the stator blades (20) in the rear row of the open rotor engine (1) are provided with a plurality of second wake controllers (80) spaced apart from the blade tip to the blade root at the trailing edge.