CN115508096A

CN115508096A - Flow channel simulation piece, anti-icing test device and anti-icing test method

Info

Publication number: CN115508096A
Application number: CN202110700549.1A
Authority: CN
Inventors: 闵现花; 武志鹏; 吴涛
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2021-06-23
Filing date: 2021-06-23
Publication date: 2022-12-23

Abstract

The invention provides a flow channel simulation piece, an anti-icing test device and an anti-icing test method. The runner simulation piece comprises an outer wall, an inner wall, a channel and a plurality of supporting pieces, wherein the outer wall is a revolving body, and the upstream end of the outer wall is used for connecting the splitter ring test piece; the inner wall is a revolving body and is positioned at the radial inner side of the outer wall; the channel is formed between the outer wall and the inner wall and is used for connecting a suction device to simulate the inner duct airflow of a compressor of the turbofan engine; a plurality of support pieces are uniformly distributed in the circumferential direction of the outer wall and the inner wall, and two ends of each support piece are respectively connected with the outer wall and the inner wall. The anti-icing test device comprises a first fan, a second fan and the flow channel simulation piece, wherein the first fan is used for simulating the outer duct airflow of the compressor of the turbofan engine, and the second fan is connected to the downstream side of the channel and used for providing the suction device. The anti-icing test method adopts the anti-icing test device, and the upstream side area and the downstream side area of the channel are designed according to the maximum suction amount of the second fan and the maximum speed of the inner duct airflow required by the test.

Description

Flow channel simulation piece, anti-icing test device and anti-icing test method

Technical Field

The invention relates to the technical field of aero-engine tests, in particular to a flow channel simulation piece, an anti-icing test device and an anti-icing test method.

Background

Because the cloud layers may contain metastable supercooled liquid water with a temperature below the freezing point, icing can easily occur on the surface of the windward part of the aircraft when the aircraft passes through the cloud layers. For air inlet parts of an aircraft engine, such as an air inlet fairing, a fan blade, an air inlet support plate, an engine splitter ring and the like, the probability of icing is higher because the airflow is accelerated and cooled under the suction action of the engine. Icing can deteriorate the starting performance of the components and cause the center of gravity of the rotating member to shift, thereby increasing vibration, which is very disadvantageous for flight safety. Therefore, anti-icing systems are commonly deployed on currently in-service aircraft and their engines.

The hot gas anti-icing system is the most mature at present and the most commonly used anti-icing system, and mainly leads hot gas out of an air system of an engine and conveys the hot gas to an inner cavity of an anti-icing component through a specific pipeline and a valve, so that the aims of increasing the surface temperature of the anti-icing component and preventing the surface of the anti-icing component from being iced are fulfilled. The anti-icing bleed air is typically bled into other air system flow paths after exiting the anti-icing chamber, or is vented directly to the outside atmosphere and to the engine main flow path.

The splitter ring of a turbofan engine is a typical anti-icing component, which is typically hot gas anti-icing in its form. In order to verify the hot-gas anti-icing effect of the splitter ring, a hot-gas anti-icing test of the splitter ring needs to be performed in an icing wind tunnel. Parameters such as the diameter of water drops in the atmosphere, the content of liquid water, the speed, the ambient temperature, the pressure and the like can be simulated in the icing wind tunnel. The test piece is placed in an icing wind tunnel, an atmospheric icing environment is simulated outside the test piece, heating measures (hot air or current) and the like are taken inside the test piece, so that the tests of wall temperature, cavity pressure and the like can be carried out, the anti-icing test is completed, and test parameters obtained by the test can be used for guiding the design of an anti-icing system of the aircraft engine.

Because the splitter ring is the part of separation engine inner duct and outer duct, in actual engine structure, the high-speed rotation of engine makes the air current flow through the upper and lower surface of splitter ring at a high speed, simultaneously because inner duct and outer duct gas flow are different, leads to the velocity of flow of the upper and lower surface of splitter ring inconsistent, is difficult to simulate the velocity of flow of the upper and lower surface of splitter ring simultaneously through the current fan of wind-tunnel.

Disclosure of Invention

One object of the present invention is to provide a flow channel simulator that can simulate the inner duct airflow of the compressor of a turbofan engine.

The runner simulation piece for achieving the purpose is used for a splitter ring anti-icing test of a turbofan engine and comprises an outer wall, an inner wall, a channel and a plurality of supporting pieces. The outer wall is a revolving body, and the upstream end of the outer wall is used for connecting a splitter ring test piece; the inner wall is a revolving body and is positioned on the radial inner side of the outer wall; said passage being formed between said outer wall and said inner wall for connection to a suction device for simulating an inner duct airflow of a compressor of said turbofan engine; the supporting pieces are uniformly distributed in the circumferential direction of the outer wall and the inner wall, and two ends of each supporting piece are connected with the outer wall and the inner wall respectively.

In one or more embodiments of the flow channel simulation piece, the flow channel simulation piece further includes a plurality of through holes, the plurality of through holes are uniformly distributed in the circumferential direction of the flow channel simulation piece and penetrate through the inner wall, the outer wall and the support piece, wherein each support piece corresponds to at least one through hole.

In one or more embodiments of the flow channel simulator, the upstream side area of the channel is larger than the downstream side area.

In one or more embodiments of the flow channel simulator, the support is an airfoil structure.

In one or more embodiments of the flow channel simulator, the leading edge to trailing edge direction of the airfoil structure is parallel to the upstream side to downstream side direction of the channel.

In one or more embodiments of the flow channel simulator, the number of the supporting members is not less than 6 and not more than 10.

In one or more embodiments of the flow channel simulator, the outer wall and the inner wall are respectively provided with an outer mounting hole and an inner mounting hole, the outer mounting hole and the inner mounting hole correspond to the cross-sectional shapes of the plurality of supporting members, and the two ends of the supporting members are respectively inserted into the outer mounting hole and the inner mounting hole and respectively welded to the outer wall and the inner wall.

In one or more embodiments of the flow channel simulator, the support member is perpendicular to the outer wall or/and the inner wall.

The runner simulation piece can simulate the runner of the booster stage of the compressor of the turbofan engine with the corresponding model, further effectively simulate the inner duct airflow of the corresponding compressor by connecting the second fan, and can achieve the flow field effect of high-speed rotation of the multi-stage rotor blades of the practical engine under the static condition, so that the gas flow velocity of the lower surface of the splitter ring test piece is consistent with the actual flow velocity under the set working condition corresponding to the anti-icing test, and the splitter ring test piece can be supported. The flow channel simulation piece is simple in structure, easy to machine, manufacture and assemble and capable of effectively reducing design, machining and test costs.

Another object of the present invention is to provide an anti-icing test apparatus that can simultaneously simulate the bypass airflow and bypass airflow of the compressor of a turbofan engine.

To achieve the object, the anti-icing test device comprises a first fan, a second fan and the flow channel simulation piece, wherein the first fan is used for simulating the bypass airflow of the compressor of the turbofan engine, the second fan is used for providing the suction device, and the second fan is connected to the downstream side of the channel.

In one or more embodiments of the anti-icing testing apparatus, the flow channel simulator further includes a plurality of through holes, the plurality of through holes are uniformly distributed in a circumferential direction of the flow channel simulator and penetrate through the inner wall, the outer wall and the support members, wherein each of the support members corresponds to at least one of the through holes, the anti-icing testing apparatus further includes a detection element, a test lead and a test stage, the detection element is disposed on the shunt ring tester, the test lead communicably connects the detection element and the test stage, and the test lead passes through one or more of the through holes.

This anti-icing test device is through adopting the outer duct air current of the compressor of the turbofan engine of first fan simulation corresponding model, and connect this runner simulation piece through setting up the second fan alone, simulate the inner duct air current of the compressor that corresponds, can make the gas velocity of flow distribution ring test piece's upper surface and lower surface unanimous with the actual velocity of flow under the established operating mode, thereby can develop the anti-icing test of flow distribution ring effectively, guarantee the accuracy of test result, improve test efficiency, and then guide the design of anti-icing system effectively, shorten aeroengine's design cycle, improve aeroengine's security and reliability. The anti-icing test device is simple in structure, easy to machine, manufacture and assemble, and capable of reducing the cost of design, machining and test.

It is yet another object of the present invention to provide an anti-icing test method that can simultaneously simulate both the bypass airflow and the bypass airflow of the compressor of a turbofan engine.

In order to achieve the anti-icing test method, the anti-icing test device is adopted, and the upstream side area and the downstream side area of the channel are designed according to the maximum suction quantity of the second fan and the maximum speed of the ducted air flow required by the test.

In one or more embodiments of the anti-icing test method, the profiles of the outer wall and the inner wall simulate the profiles of a booster stage stator case and a booster stage inner ring of the turbofan engine, respectively.

The anti-icing test method can simultaneously simulate the outer duct airflow and the inner duct airflow of the turbofan engine, so that the gas flow velocity of the upper surface and the lower surface of the splitter ring test piece is consistent with the actual flow velocity under the set working condition, the anti-icing test of the splitter ring can be effectively carried out, the accuracy of the test result is ensured, the test efficiency is improved, the design of an anti-icing system is effectively guided, the design cycle of the aero-engine is shortened, and the safety and the reliability of the aero-engine are improved.

Drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:

FIG. 1 is a partial schematic view of a compressor of a turbofan engine of a certain type.

FIG. 2 is a schematic view of an anti-icing test apparatus.

Fig. 3 and 4 are perspective views of the flow channel simulating member according to different viewing angles.

Fig. 5 is a schematic front view of the flow channel simulating member.

Fig. 6 is a side schematic view of a flow channel simulator.

Fig. 7 is a schematic cross-sectional view of a flow channel simulator.

Fig. 8 is a perspective view of the outer wall of the flow channel simulating member.

Fig. 9 is a perspective view of the inner wall of the flow channel simulator.

Fig. 10 is a perspective view of a support member of the flow channel simulating member.

Fig. 11 is a schematic cross-sectional view of a support member of the flow channel simulator.

Fig. 12 is a schematic view showing the connection relationship between the flow channel simulating member and a part of the adjacent components.

Detailed Description

The following discloses a variety of different implementation or examples implementing the subject technology. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention. It is to be noted that the drawings are designed solely as examples and are not to scale and should not be construed as limiting the scope of the invention as it may be practiced. Furthermore, some of the features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.

Fig. 1 shows a partial schematic view of a compressor 100 of a turbofan engine of a type where a splitter ring 101 is located downstream of inlet fan blades 102 of the compressor 100 to split an inlet airflow into two paths, an outer duct airflow 103 and an inner duct airflow 104, and the inner duct airflow 104 then enters a booster stage 105 located downstream of the splitter ring 101 and continues downstream of the turbofan engine 100.

The booster stage 105 includes a plurality of stages of rotor blades 106 and a plurality of stages of stator blades 107, the rotor blades 106 are mounted on a rotor disk hub 108, both radial sides of the stator blades 106 are connected to a booster stage stator casing 109 and a stator inner ring 110, respectively, the rotor disk hub 108 and the stator inner ring 110 together constitute a booster stage inner ring 111, and the bypass airflow 104 flows in a flow passage formed between the booster stage inner ring 111 and the booster stage stator casing 109.

In the description of the present invention, the terms "upstream" and "downstream" refer to relative flow directions with respect to fluid flow in a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction to which the fluid flows.

An anti-icing test apparatus 200 according to one or more embodiments of the present invention is shown in FIG. 2 and includes a wind tunnel 210 and a test stand 220. The wind tunnel 210 includes a first fan 201, a ventilation tower 202, a cooler 203, a water spray 204, a test section 205, and the like. The test section 205 includes a second fan (not shown), a diverter ring test piece (not shown), a flow channel simulation piece 400, a support device (not shown), a detection element (not shown), a test lead 206, and the like. The flow channel simulator 400 is secured within the test section 205 by a support means. The first fan 201 is used for simulating the outer duct airflow of the compressor of the turbofan engine of the type corresponding to the splitter ring test piece. The second fan is connected downstream of the flow channel simulator 400 for simulating the ducted airflow of the corresponding compressor, as will be described in detail later. The detection element is disposed on the splitter ring test piece and is communicably connected to the test bed 220 outside the wind tunnel 210 through the test leads 206.

The flow channel simulation member 400, as shown in fig. 3 to 7, includes an outer wall 1, an inner wall 2, a channel 4, and a plurality of support members 3. The outer wall 1 and the inner wall 2 are both revolution bodies, and the inner wall 2 is located on the radial inner side of the outer wall 1. The supporting pieces 3 are uniformly distributed on the circumferential direction of the outer wall 1 and the inner wall 2, and two ends 31 of each supporting piece 3 are respectively connected with the outer wall 1 and the inner wall 2. A channel 4 is formed between the outer wall 1 and the inner wall 2, and the downstream side 42 of the channel 4 is connected to a second fan to draw gas in the channel 4 by the second fan to simulate the bypass flow of a compressor of a turbofan engine of the corresponding model.

The upstream end 11 and the downstream end 12 of the outer wall 1 are both provided with an outer wall mounting edge 13 and a plurality of outer wall bolt holes 14, wherein the upstream end 11 is used for connecting a splitter ring test piece, and the downstream end 12 is used for connecting other parts in the test section 205. The axial both ends of inner wall 2 all are equipped with inner wall installation limit 21 and a plurality of inner wall bolt hole 22 for be connected with other spare parts in experimental section 205.

Referring to fig. 12, in one embodiment, the downstream end 12 of the outer wall 1 is connected to one end of a suction duct 207 through an outer wall mounting edge 13, the other end of the suction duct 207 is connected to a second fan through a bellows (not shown), and the mounting edge 21 of the inner wall 2 on the downstream side is connected to a blocking piece 208. The blocking piece 208 is used for blocking the inner wall 2 so that the second fan only sucks the gas in the channel 4, thereby improving the suction efficiency and saving the power of the second fan. Alternatively, the plug 208 is provided in the shape of a solid of revolution with a diameter that tapers from upstream to downstream, so as to provide a flow guiding effect for the gas in the channel 4. In another embodiment, the blocking piece 208 may also be provided as a one-piece structure with the inner wall 2.

Referring to fig. 3 to 7, optionally, the flow channel simulator 400 further includes a plurality of through holes 5, the plurality of through holes 5 being uniformly distributed in a circumferential direction of the flow channel simulator 400 and penetrating the outer wall 1, the inner wall 2 and the support members 3, wherein each support member 3 corresponds to at least one through hole 5. Because the anti-icing in-process needs set up more detecting element in the reposition of redundant personnel ring testpieces, and through test lead 206 with detecting element and the test bench 220 of wind-tunnel 210 outside can be connected by communication, test lead 206 directly exposes in passageway 4 and is destroyed by the high velocity air current when experimental easily, influence data transmission's stability and accuracy, even lead to the experiment to be suspended, through setting up a plurality of through-holes 5, can make test lead 206 pass from part or all through-holes 5 as required, thereby protect test lead 206, guarantee test accuracy and experimental effect, and reduce the weight of runner simulation piece 400, and simple structure, easy manufacturing.

The shape of the through hole 5 may be circular, elliptical, racetrack, or other shapes. By properly designing the number and size of the through holes 5, the requirement of protecting the test leads 206 and the strength requirement of the support 3 can be satisfied at the same time.

Alternatively, the outer wall 1, the inner wall 2 and the plurality of supporting members 3 are made of stainless steel material, so that the flow channel simulation member 400 has high rigidity and can withstand low-temperature and humid test conditions without easily failing.

The flow channel simulation piece 400 can simulate a flow channel of a pressure increasing stage of a compressor of a turbofan engine with a corresponding model, further effectively simulate the inner duct air flow of the corresponding compressor by connecting a second fan, and achieve the flow field effect of high-speed rotation of multi-stage rotor blades of an actual engine under a static condition, so that the gas flow rate of the lower surface of the splitter ring test piece is consistent with the actual flow rate under a set working condition corresponding to an anti-icing test, and the splitter ring test piece can be supported. The flow channel simulation piece 400 is simple in structure, easy to machine, manufacture and assemble, and capable of effectively reducing design, machining and test costs.

This runner simulation piece 400 sets up a plurality of support piece 3 in order to play the supporting role between outer wall 1 and inner wall 2, compares with the structure that the multistage stator blade of booster stage adoption in the actual engine supported, simple structure, easily manufacturing, the cost is lower. Optionally, the support 3 is perpendicular or nearly perpendicular to the outer wall 1 or/and the inner wall 2 to improve the support strength. The number of the supporting pieces 3 can be designed to be 6-10, so that the influence on the flow area of the channel 4 is reduced as much as possible while the requirement of supporting strength is met.

Referring to fig. 3 to 9, alternatively, the outer wall 1 and the inner wall 2 are respectively provided with an outer mounting hole 15 and an inner mounting hole 23, the outer mounting hole 15 and the inner mounting hole 23 correspond to the cross-sectional shape of the support 3, and both ends 31 of the support 3 are respectively inserted into the outer mounting hole 15 and the inner mounting hole 23 and are respectively welded to the outer wall 1 and the inner wall 2, so as to further simplify the structure of the flow channel simulator 400 for easy manufacturing. To facilitate the connection of the outer wall 1 and the inner wall 2, both ends 31 of the support member 3 may be slightly protruded radially outside the outer wall 1 and radially inside the inner wall 2.

Referring to fig. 3 to 7, 10 and 11, the support 3 is optionally of an airfoil structure to reduce the airflow resistance in the passage 4, and is simple in structure and easy to manufacture compared with a complex curved blade of an actual engine. Further, the leading edge 32 to the trailing edge 33 of the airfoil structure may be arranged substantially parallel to the upstream side 41 to the downstream side 42 of the channel 4, i.e. substantially parallel to the direction of airflow within the channel 4, thereby minimising airflow resistance within the channel 4.

This anti-icing test device 200 is through adopting first fan 201 simulation to correspond the outer duct air current of the turbofan engine's of model compressor, and connect this runner simulation piece 400 through setting up the second fan alone, simulate the inner duct air current of the compressor that corresponds, can make the gas velocity of the upper surface of splitter ring test piece and the lower surface unanimous with the actual velocity of flow under the established operating mode, thereby can launch the anti-icing test of splitter ring effectively, guarantee the accuracy of test result, improve test efficiency, and then guide the design of anti-icing system effectively, shorten aeroengine's design cycle, improve aeroengine's security and reliability. The anti-icing test device 200 is simple in structure, easy to machine, manufacture and assemble, and capable of reducing the cost of design, machining and test.

According to the anti-icing test method of one or more embodiments of the invention, the anti-icing test device 200 is adopted, and the areas of the upstream side 41 and the downstream side 42 of the channel 4 are designed according to the maximum suction amount of the second fan and the maximum speed of the bypass airflow required by the test, so that the airflow speed in the channel 4 is consistent with the set working condition, and the accuracy of the test result is improved.

Optionally, the area of the upstream side 41 of the channel 4 is greater than the area of the downstream side 42 to simulate a converging flow path for a boost stage of a turbofan engine of the corresponding model, thereby further improving the accuracy of the test results.

The outer wall 1 and the inner wall 2 have smooth surfaces and a profile determined by pneumatic analysis to ensure that the pressure loss caused by the channel 4 is minimal. Optionally, the profile of the outer wall 1 simulates a radial inner profile of a pressurizing stage stator casing of the turbofan engine of a corresponding model, and the profile of the inner wall 2 simulates a radial outer profile of a pressurizing stage inner ring of the turbofan engine of a corresponding model, so as to more accurately simulate a flow channel of the pressurizing stage of the turbofan engine of the corresponding model, and further improve the accuracy of the test result.

Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.

Claims

1. Runner analog piece for turbofan engine's splitter ring anti-icing test, its characterized in that includes:

the outer wall is a revolving body, and the upstream end of the outer wall is used for connecting the shunt ring test piece;

the inner wall is a revolving body and is positioned on the radial inner side of the outer wall;

a passage formed between the outer wall and the inner wall for connecting a suction device to simulate an inner duct airflow of a compressor of the turbofan engine; and

the supporting pieces are uniformly distributed in the circumferential direction of the outer wall and the inner wall, and two ends of each supporting piece are connected with the outer wall and the inner wall respectively.

2. The flow channel simulator of claim 1, further comprising a plurality of through holes evenly distributed around the flow channel simulator and extending through the inner wall, the outer wall and the support members, wherein each support member corresponds to at least one of the through holes.

3. The flow channel simulator of claim 1 wherein the upstream side area of the channel is greater than the downstream side area.

4. The flow channel simulator of claim 1 wherein the support member is an airfoil structure.

5. The flow channel simulator of claim 4 wherein the leading edge to trailing edge direction of the airfoil structure is parallel to the upstream side to downstream side direction of the channel.

6. The flow channel simulator of any of claims 1 to 5, wherein the number of support members is not less than 6 and not more than 10.

7. The flow channel simulating member according to any one of claims 1 to 5, wherein the outer wall and the inner wall are provided with outer mounting holes and inner mounting holes, respectively, corresponding to the cross-sectional shapes of the plurality of supporting members, and the both ends of the supporting members are inserted into the outer mounting holes and the inner mounting holes, respectively, and are welded to the outer wall and the inner wall, respectively.

8. The flow channel simulator of any of claims 1 to 5, wherein said support member is perpendicular to said outer wall or/and said inner wall.

9. Anti-icing test device comprising a first fan for simulating an bypass air flow of a compressor of said turbofan engine and a second fan for providing said suction means, said second fan being connected to a downstream side of said channel, and a flow channel simulation element according to any one of claims 1 to 8.

10. The anti-icing test device of claim 9, wherein the flow channel simulator further comprises a plurality of through holes which are uniformly distributed in a circumferential direction of the flow channel simulator and penetrate through the inner wall, the outer wall and the support members, wherein each of the support members corresponds to at least one of the through holes, the anti-icing test device further comprises a detection element, a test lead and a test bed, the detection element is disposed on the shunt ring tester, the test lead communicably connects the detection element and the test bed, and the test lead passes through one or more of the through holes.

11. Anti-icing test method, characterized in that the anti-icing test device according to claim 9 or 10 is used to design the upstream side area and the downstream side area of the channel according to the maximum suction of the second fan and the maximum velocity of the ducted air flow required for the test.

12. The anti-icing test method of claim 11, wherein said outer wall and said inner wall have profiles that mimic profiles of a booster stage stator case and a booster stage inner ring of said turbofan engine, respectively.