WO2011052566A1 - 騒音低減装置 - Google Patents
騒音低減装置 Download PDFInfo
- Publication number
- WO2011052566A1 WO2011052566A1 PCT/JP2010/068936 JP2010068936W WO2011052566A1 WO 2011052566 A1 WO2011052566 A1 WO 2011052566A1 JP 2010068936 W JP2010068936 W JP 2010068936W WO 2011052566 A1 WO2011052566 A1 WO 2011052566A1
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- Prior art keywords
- jet
- ring
- flow
- injection
- micro jet
- Prior art date
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- 238000002347 injection Methods 0.000 claims abstract description 84
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Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
- F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
- F02K1/34—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/38—Introducing air inside the jet
- F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
Definitions
- the present invention relates to a noise reduction device used for an aircraft jet engine.
- This application claims priority based on Japanese Patent Application No. 2009-247779 filed in Japan on October 28, 2009, the contents of which are incorporated herein by reference.
- An aircraft jet engine includes a fan that takes in air, a compressor that takes in and compresses a portion of the air taken in by the fan, and a combustor that mixes and burns compressed air and fuel generated by the compressor.
- the fan and the turbine that drives the compressor are sequentially arranged by the combustion gas of the combustor.
- the compressor, the combustor, and the turbine are installed in a main nozzle that is a cylindrical partition wall, and the fan is installed on the upstream side of the main nozzle.
- Most of the air taken in by the fan passes through a bypass passage provided between the casing and the casing covering the outer periphery of the main nozzle.
- the air (bypass flow) that has passed through the bypass channel is discharged so as to surround the outer periphery of the turbine core flow (jet flow), and merges with the jet flow.
- a region where the jet flow and the bypass flow merge serves as a noise generation source to generate noise.
- Various techniques have been disclosed for reducing this noise.
- a so-called chevron nozzle in which the shape of the bypass passage outlet peripheral portion of the casing (engine nacelle) and the jet flow passage outlet peripheral portion of the main nozzle is formed in a saw shape, the inner peripheral surface side and the outer peripheral surface side of the main nozzle Has been disclosed (see, for example, Patent Document 1).
- Patent Document 2 discloses a system and method for reducing exhaust noise of a jet engine nozzle having a protrusion (chevron).
- a first flow of gas is generated by a jet engine, and the first flow is delivered through a nozzle having a trailing edge circumference including a plurality of protrusions extending in the rear direction, and is pressurized. Injecting a second stream of fluid into the first stream proximate the protrusion.
- Patent Document 3 discloses an apparatus for reducing jet engine exhaust noise using a vibrating jet.
- a technique in which a plurality of pipes communicating with a fan part or a compressor are laid around the main nozzle, and the tip parts of these pipes are configured as nozzles for ejecting a part of compressed air (for example, non- Patent Document 1). Then, the micro jet is jetted from the nozzle configured in this way toward the junction of the jet flow and the bypass flow. According to this, the jet flow and the bypass flow are suitably mixed by the generation of the vortex by the microjet, and noise can be further reduced.
- Patent Document 1 there is a problem that a pressure loss occurs because a speed difference is generated by the chevron nozzle. This problem is the same in Patent Document 2, even if the exhaust noise of the jet engine can be reduced by injecting the second flow of the pressurized fluid into the first flow close to the protrusion. Since the subject is a jet engine with a chevron nozzle, the problem of creating a pressure loss still exists.
- Patent Document 3 a channel that guides an oscillating flow to flow toward the engine exhaust gas is constituted by a small-diameter pipe. For this reason, the pressure loss in the small-diameter channel increases, and it is practically difficult to supply a vibration flow that can effectively reduce engine exhaust noise. In addition, it is necessary to attach an additional device such as a flow control valve or a flow stabilizer to the channel for guiding the oscillating flow. For this reason, the number of parts constituting the apparatus increases, the structure of the apparatus becomes complicated, and the assembly workability decreases.
- an additional device such as a flow control valve or a flow stabilizer
- Non-Patent Document 1 there is a possibility that the pipe for guiding the compressed air expands due to the heat of the jet engine and is damaged. Further, a cavity flow is generated around the pipe, and fluid noise is generated, or additional noise accompanying vibration of the pipe is generated. Then, there is a possibility that the nozzle injection angle changes due to the microjet injection thrust and a predetermined noise reduction effect cannot be obtained. For this reason, in order to maintain the nozzle injection angle at a desired angle, a stay for fixing the nozzle is required. As a result, the main nozzle becomes larger, the nacelle loss increases with the increase in size, and additional noise is generated. The problem arises. Moreover, high accuracy is required for the assembly work for fixing each nozzle to a desired injection angle, and it is difficult to obtain a desired noise reduction effect.
- the present invention has been made in view of the above-described circumstances, and provides a noise reduction device that can prevent nozzle damage and efficiently reduce noise. It is another object of the present invention to provide a noise reduction device that can improve assembly workability and can reliably obtain a noise reduction effect.
- a noise reduction device is provided with a micro jet ring having a plurality of injection pipes formed at equal intervals in a circumferential direction at a jet side peripheral edge of a main nozzle of a jet engine.
- a supply path for introducing a part of compressed air from a flow path upstream of the combustor to the plurality of injection pipes is provided, and the plurality of injection pipes eject part of the compressed air from the main nozzle. It is made to inject toward the jet stream made.
- the microjet can be directed toward the junction of the jet flow and the bypass flow using a plurality of injection pipes formed in the micro jet ring without using the nozzle of the pipe as in the prior art. Can be injected. For this reason, compared with the case where the nozzle of piping is used, while the rigidity of a micro jet injection part can be improved, the injection angle of an injection pipe does not change with micro jet injection thrust. Therefore, it is possible to prevent the micro jet ring from being damaged while reducing the size of the main nozzle, to easily maintain the injection angle, and to efficiently reduce noise. Moreover, since the rigidity can be increased, the diameter of the injection tube can be set large, and the pressure loss can be reduced.
- micro jet injection can be performed more efficiently, and noise can be reduced effectively. Further, since no pipe is provided in the micro jet injection portion, the external flow cavity can be prevented, and the generation of additional noise can be suppressed. And micro jet injection is realizable only by attaching a micro jet ring to the jetting side periphery of a main nozzle. For this reason, it becomes possible to improve assembly workability.
- the noise reduction device is formed such that the diameter of the micro jet ring is reduced from the upstream side to the downstream side of the jet flow, and at the discharge side periphery of the micro jet ring, An arcuate surface portion is formed over the entire circumference so that the inner circumferential surface of the microjet ring increases in diameter toward the tip.
- the start position of the arc-shaped surface portion of the micro jet ring that is, the upstream end of the arc-shaped surface portion can be set to the throat of the main nozzle (the point where the inner diameter of the main nozzle is most reduced). .
- microjet injection can be performed immediately after the jet flow passes through the throat.
- the pressure in the main nozzle is too high, and it becomes difficult to secure the flow rate of the micro jet injection.
- the set flow rate of the engine calculated in the throat portion is changed. For this reason, according to this invention, it becomes possible to perform microjet injection to an efficient position, and it can reduce noise more efficiently.
- the noise reduction device is characterized in that it is formed in the downstream direction so that at least the vicinity of the jet outlet side of the plurality of jet pipes forms an acute angle with respect to the axial direction of the main nozzle. .
- the noise reduction device is characterized in that a chamber is provided between the micro jet ring and the flow path so as to communicate the micro jet ring and the flow path.
- a micro jet is jetted toward a junction of a jet flow and a bypass flow using a plurality of jet pipes formed in a micro jet ring without using a pipe nozzle as in the prior art.
- the injection angle of an injection pipe does not change with micro jet injection thrust. Therefore, it is possible to prevent the micro jet ring from being damaged while reducing the size of the main nozzle, to easily maintain the injection angle, and to efficiently reduce noise.
- the rigidity can be increased, the diameter of the injection tube can be set large, and the pressure loss can be reduced.
- micro jet injection can be performed more efficiently, and noise can be reduced effectively. Further, since the pipe is not provided in the micro jet injection portion, the cavity flow in this portion can be prevented, and the generation of additional noise can be suppressed. And micro jet injection is realizable only by attaching a micro jet ring to the ejection side periphery of a main nozzle. For this reason, the assembly work for fixing each nozzle to a desired injection angle becomes unnecessary, and the assembly workability can be improved.
- FIG. 1 is a schematic cross-sectional view showing a schematic configuration of a jet engine in an embodiment of the present invention. It is a perspective view of the noise reduction apparatus in the embodiment of the present invention.
- FIG. 3 is a cross-sectional view taken along line AA in FIG. 2. It is the B section enlarged view of FIG.
- It is a schematic sectional drawing which shows other embodiment of the noise reduction apparatus of this invention.
- FIG. 1 is a schematic cross-sectional view showing a schematic configuration of a jet engine 100 to which a noise reduction device 1 according to the present invention is applied.
- the jet engine 100 includes a cylindrical casing 2, a cylindrical partition wall 3 that is partly protruded from the ejection side peripheral edge (rear edge) 2 a of the casing 2, and upstream of the casing 2.
- the fan unit 11, the compressor 4, the combustor 12, and the turbine 13 are sequentially arranged along the central axis C1 from the side to the downstream side.
- the noise reduction device 1 is provided on the jet side (the right side in FIG. 1) of the cylindrical partition wall 3 of the jet engine 100.
- Inside the cylindrical partition wall 3 is a flow path 5 through which a high-speed jet stream X flows.
- a space 6 between the cylindrical partition wall 3 and the casing 2 is a flow path 6 through which a low-speed bypass flow Y flows.
- the casing 2 and the cylindrical partition wall 3 of the jet engine 100 have a function as an engine nacelle that forms the outer shape of the jet engine 100.
- the casing 2 partially covers the outer periphery of the cylindrical partition wall 3.
- the opening on the upstream side of the casing 2 functions as an air intake port 2A for taking in air A, while the opening on the downstream side of the casing 2 functions as a bypass flow discharge port 2B for discharging the bypass flow Y.
- the bypass flow Y is the low-speed fluid that flows between the cylindrical partition wall 3 and the casing 2 and is the air A that is not taken into the compressor 4 out of the air A that is taken in from the air intake port 2A.
- the jet flow X is a fluid that is exhausted from the turbine 13 and flows in the cylindrical partition wall 3, and is a fluid that is faster than the bypass flow Y.
- An external airflow Z flows along the outer peripheral surface of the casing 2. That is, the external airflow Z is a low-speed fluid that flows outside the bypass flow Y.
- the cylindrical partition wall 3 is arranged slightly downstream along the central axis C1 direction with respect to the casing 2, and partitions the flow path 5 through which the jet flow X flows and the flow path 6 through which the bypass flow Y flows.
- a fan 11 a is installed near the upstream end in the casing 2 and upstream of the cylindrical partition wall 3.
- the fan 11a takes in air A from the outside.
- a compressor 4 is installed in the cylindrical partition wall 3 on the downstream side of the fan 11a. The compressor 4 takes in a part of the air A taken in by the fan 11a and compresses it.
- a combustor 12 is installed in the cylindrical partition wall 3 on the downstream side of the compressor 4.
- the combustor 12 mixes fuel with the air A compressed by the compressor 4 and burns it, and discharges combustion gas.
- a turbine 13 is disposed in the cylindrical partition wall 3 on the downstream side of the combustor 12. The turbine 13 drives the fan 11 a and the compressor 4 with the combustion gas discharged from the combustor 12.
- the casing 2 and the cylindrical partition wall 3 of the jet engine 100 configured as described above are suspended from a wing of an aircraft (not shown) via a pylon 8 extending downstream of the jet flow X and the bypass flow Y.
- the pylon 8 is a member that extends in a direction orthogonal to the casing 2 and the central axis C ⁇ b> 1 of the cylindrical partition wall, and has a protruding portion 8 ⁇ / b> A that extends downstream from the casing 2.
- the cylindrical partition wall 3 functions as a main nozzle that discharges the jet stream X, and a micro jet ring 16 that constitutes a part of the noise reduction device 1 is provided on the ejection side periphery (rear edge) 3A of the cylindrical partition wall 3. Is provided. That is, the opening on the downstream side of the micro jet ring 16 functions as a jet flow discharge port 16A for discharging the jet flow X.
- the noise reduction device 1 includes a micro jet ring 16 provided on the ejection side periphery 3A of the cylindrical partition wall 3, and an upstream side of the micro jet ring 16 (the left side in FIGS. 1 and 2). And a chamber 17 provided on the outer periphery of the cylindrical partition wall 3.
- the chamber 17 is formed of stainless steel (for example, SUS321), Inconel, or the like, and has a cylindrical inner peripheral wall portion 18 that constitutes a part of the inner peripheral portion of the cylindrical partition wall 3. That is, the inner peripheral wall portion 18 is formed in a substantially truncated cone shape in a side view that is reduced in diameter toward the ejection side (downstream side), and is flush with the inner peripheral surface of the cylindrical partition wall 3.
- An outer flange portion 18 a is integrally formed on the upstream peripheral edge of the inner peripheral wall portion 18.
- the outer flange portion 18a is a member for fixing the inner peripheral wall portion 18 to the cylindrical partition wall 3, and a plurality of bolt holes (not shown) are formed at equal intervals in the circumferential direction.
- a female screw part is engraved at a position corresponding to the bolt hole of the cylindrical side wall 3, and by screwing a bolt (not shown) from the inner peripheral wall part 18 side, the inner peripheral wall part 18 is It can be fastened and fixed to the cylindrical partition wall 3.
- a plurality of air intake ports 19 are formed at equal intervals in the circumferential direction so as to avoid unillustrated bolt holes.
- the air intake 19 is connected to the flow path 5 on the upstream side of the combustor 12 via a supply path 20 provided in the cylindrical partition wall 3.
- One end of the supply path 20 is connected to the air intake port 19 of the outer flange portion 18a through a joint (not shown). Thereby, a part of the air A compressed by the fan 11 a or the compressor 4 is taken into the chamber 17.
- a valve 21 is provided in the supply path 20.
- a Teflon (registered trademark) tube or the like is used as the supply path 20. By using a Teflon (registered trademark) tube, it is possible to improve the assembly workability and reduce piping loss.
- a cylindrical outer peripheral wall portion 22 is provided on the outer peripheral side of the inner peripheral wall portion 18 so as to cover the inner peripheral wall portion 18.
- the outer peripheral wall portion 22 is formed in a substantially truncated cone shape in a side view so as to extend along the extending direction of the inner peripheral wall portion 18, and constitutes a part of the outer peripheral portion of the cylindrical partition wall 3. That is, the outer diameter of the upstream end portion of the outer peripheral surface of the outer peripheral wall portion 22 matches the outer diameter of the downstream end portion of the outer peripheral surface of the cylindrical partition wall 3 (see FIG. 1).
- the upstream peripheral portion of the outer peripheral wall portion 22 is fixed to the outer flange portion 18a of the inner peripheral wall portion 18 by machining or welding. Part of the air A compressed by the fan 11a or the compressor 4 is taken into the space K surrounded by the outer peripheral wall portion 22 and the inner peripheral wall portion 18 thus fixed.
- a micro jet ring 16 is stamped into an opening 17A formed on the downstream side of the chamber 17, that is, on the ejection side of the cylindrical partition wall 3 and formed by the inner peripheral wall portion 18 and the outer peripheral wall portion 22. . Similar to the chamber 17, the micro jet ring 16 is formed in a substantially annular shape using stainless steel (for example, SUS321), Inconel, or the like. The micro jet ring 16 is formed to be tapered toward the downstream side.
- the inner peripheral surface 16a of the micro jet ring 16 is formed to be flush with the inner peripheral surface of the chamber 17 and to decrease in diameter toward the downstream side along the inner peripheral surface of the chamber 17.
- the outer peripheral surface 16b of the micro jet ring 16 is formed so as to curve inward in the radial direction toward the downstream side.
- the outer peripheral surface 16 b is flush with the outer peripheral wall portion 22 of the chamber 17.
- the micro jet ring 16 has a wall thickness on the base end side, and becomes thinner toward the tip end side.
- an insertion portion 23 having a substantially annular shape in a plan view in the axial direction is integrally formed.
- the insertion portion 23 is fitted into the opening 17A of the chamber 17 by stamping.
- O-ring grooves 24a and 24b are formed on the inner peripheral surface and the outer peripheral surface of the insertion portion 23, respectively.
- O-rings 25 for improving the sealing performance of the connecting portion between the chamber 17 and the micro jet ring 16 are mounted.
- the O-ring 25 it is desirable to use a rubber, fluorine-based, Teflon (registered trademark) -based one having a heat resistant temperature of about 400 ° C.
- a plurality of injection pipes 26 penetrating in the axial direction are formed at equal intervals in the circumferential direction.
- the injection pipe 26 injects the air A taken into the chamber 17 toward the jet flow X discharged from the jet flow discharge port 16A.
- the injection pipe 26 extends from the insertion portion 23 to the front of the approximate center of the micro jet ring 16 in the axial direction, and extends along the extending direction of the inner peripheral surface 16a.
- the second tube 26b is formed from the tip of the one tube 26a toward the tip of the micro jet ring 16.
- the inclination angle ⁇ of the second pipe 26b is set to be steeper than the first pipe 26a. More specifically, the inclination angle ⁇ of the second pipe 26b is set to 30 to 45 degrees with respect to the central axis C1 (see FIG. 4).
- the air A taken in the chamber 17 is surely injected into the jet flow X discharged from the jet flow discharge port 16A, and the inclination gradient of the outer peripheral surface 16b of the micro jet ring 16 is gently reduced. can do. Since the plurality of injection pipes 26 are formed in the micro jet ring 16 at equal intervals in the circumferential direction, the air A injected from each injection pipe 26 becomes a micro jet and is jetted toward the jet stream X.
- an arcuate surface portion 27 having a substantially arc-shaped cross section is formed at the tip of the micro jet ring 16.
- the tip of the micro jet ring 16 and the inner peripheral surface 16a side expands from the starting point P of the arcuate surface portion 27 toward the ejection side (right side in FIG. 4). It will be in the state formed. That is, the inner peripheral surface 16a of the micro jet ring 16 is reduced in diameter toward the ejection side. For this reason, the starting point P of the arcuate surface portion 27 is set to the throat SP having the smallest diameter.
- a jet flow flows through the flow path 5 in the cylindrical partition wall 3 and is discharged from the jet flow discharge port 16A.
- the bypass flow Y flows through the flow path 6 between the cylindrical partition wall 3 and the casing 2 and is discharged from the bypass flow outlet 2B.
- the valve 21 is opened and a part of the air A compressed by the fan 11 a or the compressor 4 is taken into the chamber 17.
- the air A in the chamber 17 increases to a predetermined pressure, the air A is microjetted toward the jet stream X through the jet pipe 26 of the microjet ring 16.
- FIG. 5 is an explanatory diagram showing the flow of the jet stream X and the air A during microjet injection.
- the jet stream X is a region where the pressure is higher on the upstream side than the throat SP.
- the downstream side of the throat SP is a lower pressure region than the upstream side. Therefore, since the micro jet injection is performed toward a low pressure region, a sufficient flow rate can be secured without increasing the pressure in the chamber 17 more than necessary. Then, immediately after the throat SP, that is, the micro jet injection is smoothly performed in the downstream direction so as to form an acute angle with respect to the axial direction from the throat SP.
- the pressure difference between the chamber 17 and the supply path 20 connecting the chamber 17 and the flow path 5 upstream of the combustor 12. Can be reduced.
- the pressure loss of the air A in the supply path 20 can be reduced, and the path in which the pressure loss occurs can be substantially limited only to the injection pipe 26 of the micro jet ring 16.
- the jet engine 100 is driven, the temperature of each component rises, but the amount of thermal expansion of the micro jet ring 16 can be suppressed to be smaller than that of a nozzle using a conventional pipe. For this reason, the amount of change in the diameter of the injection pipe 26 formed in the micro jet ring 16 is also smaller than in the prior art, and it is difficult to reduce the flow rate of the air A injected through the injection pipe 26.
- the microjet-injected air A reaches the region where the discharged jet stream X and the bypass stream Y merge and mixes them appropriately. Thereby, the noise produced by the merge of the jet flow X and the bypass flow Y is reduced.
- noise can be more efficiently reduced by setting the number of injection pipes 26 formed on the micro jet ring 16 based on the following equation.
- the diameter of the injection pipe 26 is d
- the diameter at the throat SP of the micro jet ring 16 that is, the diameter of the injection nozzle of the jet stream X
- the number of the injection pipes 26 is n
- the design index is ⁇ .
- the injection pipe 26 is formed in the micro jet ring 16, the injection angle of the injection pipe 26 is not changed by the micro jet injection thrust. For this reason, since it is not necessary to reinforce separately in order to maintain an injection angle, size reduction of the micro jet ring 16 can be achieved. As a result, the cylindrical partition wall 3 can be downsized. Furthermore, since the micro jet ring 16 is used instead of the conventional piping, the cavity flow due to the piping can be prevented and the generation of additional noise can be suppressed.
- the position of a micro jet injection port does not change only by forming the several injection pipe 26 in the micro jet ring 16 at equal intervals in the circumferential direction. For this reason, peeling of micro jet injection can be prevented and noise can be reduced efficiently.
- the assembly of the micro jet ring 16 can be completed simply by forming the insertion portion 23 integrally with the micro jet ring 16 and fitting the insertion portion 23 into the opening 17 A of the chamber 17. For this reason, the assembly workability of the jet engine 100 can be improved.
- the micro jet ring 16 is formed in a substantially truncated cone shape when viewed from the side, and an arcuate surface portion 27 is formed at the tip of the micro jet ring 16. For this reason, the starting point P of the arcuate surface portion 27 can be set to the throat SP, and microjet can be ejected from the throat SP toward the jet flow. Therefore, it becomes possible to perform microjet injection efficiently, and noise can be reduced more efficiently.
- the injection pipe 26 formed on the micro jet ring 16 is composed of a first pipe 26a and a second pipe 26b, and the inclination angle ⁇ of the second pipe 26b is set larger than the inclination angle of the first pipe 26a. is doing. For this reason, the inclination gradient of the outer peripheral surface 16b of the micro jet ring 16 can be made gentle, and the nacelle resistance of the jet engine 100 can be reduced. As a result, the aerodynamic performance of the jet engine 100 can be improved.
- the chamber 17 that connects the micro jet ring 16 and the flow path 5 is provided between the micro jet ring 16 and the flow path 5 upstream of the combustor 12, the chamber 17 and the chamber 17 And the supply path 20 connecting the flow path 5 can be reduced, the pressure loss of the air A in the supply path 20 can be reduced, and the path in which the pressure loss occurs is the injection pipe 26 of the micro jet ring 16. It can be almost limited to only. For this reason, since the pressure loss is reduced, it is possible to efficiently perform the micro jet injection from the injection pipe 26, and it is possible to reduce noise more efficiently.
- FIG. 6 shows the result of verifying the effect of reducing the pressure loss by providing the chamber 17 for communicating the micro jet ring 16 and the flow path 5 in the noise reduction device 1 according to the present embodiment.
- the verification result shown in FIG. 6 shows that the part from the flow path 5 upstream of the combustor 12 to the injection pipe 26 of the micro jet ring 16 through the chamber 17 is extracted, and the total pressure loss coefficient (% ).
- the horizontal axis represents the axial position
- the vertical axis represents the total pressure loss coefficient (%).
- the verification shown in FIG. 6 was performed by numerically analyzing the total pressure loss coefficient at each axial position under the following conditions.
- Inner diameter of flow path 5 ⁇ 5 mm
- the total pressure loss coefficient increases rapidly at a position where the connection position of the chamber 17 and the injection pipe 26, that is, the position in the axial direction is 0.1 (m). This is thought to be because the total pressure loss increased because the injection pipe 26 had a smaller cross-sectional area than the chamber 17 having a large cross-sectional area. However, since the injection pipe 26 has a small cross-sectional area, even if the total pressure loss rapidly increases as shown in FIG. 6, the increase in the total pressure loss at the injection pipe outlet 26 is only about 10% to 20%.
- the flow path 5 and the chamber are similar to the increase in the total pressure loss at the axial position 0.1 (m) shown in FIG.
- the total pressure loss suddenly increases from the position of the axial connection position ⁇ 0.18 (m) which is the connection position of 17.
- the total pressure loss at the outlet of the injection pipe 26 decreases to 50 (%). It is clear that it exceeds.
- the presence of the chamber 17 is a mechanism that is indispensable for actually performing microjet injection in an aircraft engine. This is because the presence of the chamber 17 can suppress the total pressure loss according to the chamber part volume.
- the noise reduction device according to the present embodiment since the chamber 17 is provided, the loss of the extraction pressure from the engine for injecting the microjet is greatly reduced, and a large amount of extraction from the compressor is performed. The effect of not requiring is obtained.
- the present invention is not limited to the above-described embodiment, and includes various modifications made to the above-described embodiment without departing from the spirit of the present invention.
- the insertion portion 23 is integrally formed at the base end of the micro jet ring 16, and the O-ring 25 is attached to the inner peripheral surface and the outer peripheral surface of the insertion portion 23, respectively.
- the case where a seal stamp is fitted into the opening 17A has been described.
- the present invention is not limited to this, and the micro jet ring 16 and the chamber 17 may be connected by the configuration shown in FIG.
- FIG. 7 is a schematic cross-sectional view showing another embodiment of the noise reduction device 1.
- step surfaces 28 and 29 are formed on the opening portion 17A side so as to be thin.
- the insertion portion 23 formed integrally with the micro jet ring 16 is formed so as to correspond to the step surfaces 28 and 29 and can be fitted to the step surfaces 28 and 29.
- a female thread portion 32 is engraved on the step surface 28 of the inner peripheral wall portion 18 along the thickness direction.
- bolt holes 33 and 34 penetrating in the thickness direction are formed in the portions corresponding to the stepped surface 29 of the outer peripheral wall portion 22 and the female screw portion 32 of the insertion portion 23.
- the chamber 17 and the micro jet ring 16 can be connected by inserting bolts (not shown) into the bolt holes 33 and 34 and screwing them into the female screw portions 32 of the inner peripheral wall portion 18.
- the insertion portion 23 is not formed with O-ring grooves 24a and 24b on the inner peripheral surface and the outer peripheral surface.
- a metal-based seal member 31 is mounted between the insertion portion 23 and the step portion 28 a of the inner peripheral wall portion 18.
- an O-ring 25 is mounted between the insertion portion 23 and the step portion 29 a of the outer peripheral wall portion 22.
- the seal member 31 and the O-ring 25 With the seal member 31 and the O-ring 25, the sealing performance of the connection portion between the chamber 17 and the micro jet ring 16 can be improved.
- the seal member 31 a metal seal using a heat-resistant alloy, the heat-resistant temperature of the seal member 31 can be set to about 800 ° C.
- a C ring, an E ring, a U ring, or the like can be used.
- micro jet ring 16 and the chamber 17 are configured separately has been described.
- the present invention is not limited to this, and the micro jet ring 16 and the inner peripheral wall portion 18 of the chamber 17 may be integrally formed as shown in FIG.
- FIG. 8 is a schematic cross-sectional view showing another embodiment of the noise reduction device 1.
- the inner peripheral surface 16 a side of the micro jet ring 16 is integrally formed at the downstream end (the right end in FIG. 8) of the inner peripheral wall portion 18 of the chamber 17.
- the recessed part 35 is formed over the perimeter by the micro jet ring 16, the inner peripheral wall part 18 of the chamber 17, and the outer flange part 18a.
- the recess 35 is closed by the outer peripheral wall portion 22 of the chamber 17.
- a recess 36 that can receive the tip of the outer peripheral wall portion 22 is formed over the entire circumference at a portion corresponding to the tip of the outer peripheral wall portion 22. And while fixing the front-end
- the present invention is not limited to this, and one end of the supply path 20 may be extended to the micro jet ring 16 instead of the chamber 17. In this case, one end of the supply path 20 and the micro jet ring 16 are connected via a joint or the like.
- the micro jet ring 16 is formed in a substantially annular shape.
- the present invention is not limited to this, and the micro jet ring 16 may be divided in the circumferential direction. In this case, airtightness is secured by using a seal member or the like on the mating surface of each ring piece (not shown) formed by dividing the micro jet ring 16.
- the injection pipe 26 may be formed on each ring piece, or a groove may be formed on the mating surface of each ring piece, and the injection pipe 26 may be configured by overlapping the grooves.
- the noise reduction device can prevent the nozzle from being damaged and can efficiently reduce the noise. Moreover, according to the noise reduction device according to the present invention, it is possible to improve the assembly workability and reliably obtain the noise reduction effect.
- Noise reduction device 2 Casing 3 Tubular partition (main nozzle) 3A ejection side peripheral edge 4 compressor 5 flow path 12 combustor 16 micro jet ring 16A jet flow discharge port 17 chamber 20 supply path 26 injection pipe 26a first pipe 26b second pipe 27 arcuate surface portion 100 jet engine A air X jet flow
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Abstract
Description
本願は、2009年10月28日に、日本に出願された特願2009-247779号に基づき優先権を主張し、その内容をここに援用する。
圧縮機、燃焼器、およびタービンは、筒状隔壁である主ノズル内に設置され、ファンは、主ノズルの上流側に設置されている。ファンが取り入れた空気の大部分は、主ノズルの外周を覆うケーシングとの間に設けられたバイパス流路を通る。このバイパス流路を通った空気(バイパス流)は、タービンのコア流(ジェット流)の外周を囲むように排出されて、ジェット流と合流する。
例えば、ケーシング(エンジンナセル)のバイパス流路出口周縁部、および主ノズルのジェット流路出口周縁部の形状を鋸状に形成した所謂シェブロンノズルとし、主ノズルの内周面側、および外周面側を流れる流体を効率よく混合させて騒音を低減する技術が開示されている(例えば、特許文献1参照)。
さらに、配管の周囲にキャビティ流れが生じ流体騒音が発生、もしくは配管の振動に伴う付加騒音が発生する。
そして、マイクロジェット噴射推力によりノズルの噴射角度が変化し、所定の騒音低減効果が得られない可能性がある。このため、ノズルの噴射角度を所望の角度に維持すべく、ノズルを固定するステーなどが必要となり、この分、主ノズルが大型化すると共に、大型化に伴うナセル損失の増加、付加騒音の発生という問題が生じる。
また、各ノズルを所望の噴射角度に固定するための組み立て作業には高い精度が必要で、所望の騒音低減効果を得ることが難しい。
また、組み立て作業性を向上でき、騒音低減効果を確実に得ることが可能な騒音低減装置を提供するものである。
また、剛性を高めることができる分、噴射管の直径を大きく設定することができ、圧力損失を低減できる。このため、より効率よくマイクロジェット噴射を行うことができ、効果的に騒音を低減できる。
さらに、マイクロジェット噴射部分に配管を設けない分、外部流のキャビティを防止でき、付加騒音の発生を抑制できる。
そして、マイクロジェットリングを主ノズルの噴出側周縁に取り付けるだけでマイクロジェット噴射を実現することができる。このため、組み立て作業性を向上させることが可能になる。
ここで、スロート通過前にマイクロジェット噴射を行おうとすると、主ノズル内の圧力が高すぎるので、マイクロジェット噴射の流量を確保するのが困難になる。更に、マイクロジェットによる流量をスロート通過前に与えると、スロート部で計算されるエンジンの設定流量を変えてしまう。このため、本発明によれば、効率のよい位置にマイクロジェット噴射を行うことが可能になり、さらに効率よく騒音を低減することができる。
このように構成することで、少なくともマイクロジェットリングの噴出口側近傍の肉厚を、先端に向かうに従って薄肉形状にすることが可能になる。このため、ジェットエンジンのナセル抵抗が低減でき、ジェットエンジンの空力性能を高めることが可能になる。
このように構成することで、流路からマイクロジェットリングに至る間を通る圧縮空気の流路スペースを大きく確保することができる。このため、圧力損失を低減することができ、より効率よく各噴射管からマイクロジェットを噴射させることが可能になる。
さらに、チャンバを設けることによって、このチャンバに対応する部分の主ノズルの外表面を滑らかに形成することができる。このため、キャビティ流れをより確実に防止し、かつジェットエンジンのナセル抵抗を低減することができる。
また、剛性を高めることができる分、噴射管の直径を大きく設定することができ、圧力損失を低減できる。このため、より効率よくマイクロジェット噴射を行うことができ、効果的に騒音を低減できる。
さらに、マイクロジェット噴射部分に配管を設けない分、この部分のキャビティ流れを防止でき、付加騒音の発生を抑制できる。
そして、マイクロジェットリングを主ノズルの噴出側周縁に取り付けるだけでマイクロジェット噴射を実現することができる。このため、各ノズルを所望の噴射角度に固定するための組み立て作業が不要となり、組み立て作業性を向上させることができる。
次に、この発明の実施形態を図面に基づいて説明する。
図1は、本発明に係る騒音低減装置1が適用されたジェットエンジン100の概略構成を示す、模式断面図である。
図1に示すように、ジェットエンジン100は、筒状のケーシング2と、ケーシング2の噴出側周縁(後縁)2aから一部が突出して内挿される筒状隔壁3と、ケーシング2内に上流側から下流側へ中心軸線C1に沿って順次配列された、ファン部11、圧縮機4、燃焼器12、およびタービン13とを備える。また、ジェットエンジン100の、筒状隔壁3の噴出側(図1における右側)には、騒音低減装置1が設けられている。
筒状隔壁3内は、高速のジェット流Xが流れる流路5とされる。筒状隔壁3とケーシング2との間は、低速のバイパス流Yが流れる流路6とされる。
ケーシング2の上流側の開口は、空気Aを取り入れる空気取入口2Aとして機能する一方、ケーシング2の下流側の開口は、バイパス流Yを排出するバイパス流排出口2Bとして機能している。
ケーシング2内の上流側端部近傍であって筒状隔壁3の上流には、ファン11aが設置されている。ファン11aは、外部から空気Aを取り入れる。
ファン11aよりも下流側であって筒状隔壁3内には、圧縮機4が設置されている。圧縮機4は、ファン11aが取り入れた空気Aの一部を取り込んで圧縮する。
燃焼器12よりも下流側であって筒状隔壁3内には、タービン13が配置されている。タービン13は、燃焼器12が排出する燃焼ガスによって、ファン11a、および圧縮機4を駆動する。
パイロン8は、ケーシング2、および筒状隔壁の中心軸線C1と直交する方向に延在する部材であって、ケーシング2よりも下流側に延びる突出部8Aを有している。
図2は、騒音低減装置1の斜視図、図3は、図2のA-A線に沿う断面図、図4は、図3のB部拡大図である。
図1~図4に示すように、騒音低減装置1は、筒状隔壁3の噴出側周縁3Aに設けられたマイクロジェットリング16と、マイクロジェットリング16の上流側(図1、図2における左側)であって筒状隔壁3の外周部に設けられたチャンバ17とを有している。
すなわち、内周壁部18は、噴出側(下流側)に向かうにしたがって縮径された側面視略円錐台状に形成されており、筒状隔壁3の内周面と面一になっている。
内周壁部18の上流側周縁には、外フランジ部18aが一体成形されている。この外フランジ部18aは、内周壁部18を筒状隔壁3に固定するための部材で、複数のボルト孔(不図示)が周方向に等間隔に形成されている。一方、筒状側壁3のボルト孔に対応する位置には、雌ネジ部が刻設されており、ここに内周壁部18側から不図示のボルトを螺入することによって、内周壁部18を筒状隔壁3に締結固定できる。
この空気取入口19は、筒状隔壁3に設けられている供給路20を介して燃焼器12よりも上流側の流路5に接続されている。供給路20は、この一端が不図示の継手を介して外フランジ部18aの空気取入口19に接続されている。これにより、ファン11a又は圧縮機4が圧縮した空気Aの一部がチャンバ17に取り込まれる。また、供給路20の途中には、バルブ21が設けられている。
なお、供給路20としては、例えば、テフロン(登録商標)チューブ等が用いられる。
テフロン(登録商標)チューブを用いることにより、組み付け作業性を向上できると共に、配管損失を低減することが可能になる。
外周壁部22の上流側周縁部は、内周壁部18の外フランジ部18aに機械加工、又は溶接により固定されている。このように固定された外周壁部22と内周壁部18とで取り囲まれる空間Kに、ファン11a又は圧縮機4が圧縮した空気Aの一部が取り込まれる。
マイクロジェットリング16は、チャンバ17と同様にステンレス(例えば、SUS321)やインコネル等で略円環状に形成される。マイクロジェットリング16は、下流側に向かうに従って先細りとなるように形成されている。
Oリング25としては、ゴム、フッ素系、およびテフロン(登録商標)系等、耐熱温度が約400℃程度あるものを用いることが望ましい。
マイクロジェットリング16に複数の噴射管26が周方向に等間隔で形成されていることから、各噴射管26から噴射された空気Aはマイクロジェットとなってジェット流Xに向かって噴射される。
すなわち、マイクロジェットリング16の内周面16aが噴出側に向かうに従って縮径されている。このため、弧状面部27の開始点Pが最も縮径されたスロートSPに設定される。
次に、ジェットエンジン100、および騒音低減装置1の作用について説明する。
図1に示すように、航空機の離陸時には、まず、ファン11aを回転させて空気取入口2Aから空気Aを取り入れる。この空気Aの一部は、圧縮機4により圧縮され、燃焼器12にて燃料と混合されて燃焼される。
タービン13では、燃焼器12から排出された燃焼ガスによってファン11a、および圧縮機4の駆動力が発生する。以降は、タービン13によって発生した駆動力によって、ファン11aが回転して空気Aが取り込まれていく。
このとき、バルブ21を開いてファン11a又は圧縮機4で圧縮された空気Aの一部をチャンバ17内に取り込む。そして、チャンバ17内の空気Aが所定の圧力まで高まると、この空気Aがマイクロジェットリング16の噴射管26を介してジェット流Xに向かってマイクロジェット噴射される。
図5において、ジェット流XはスロートSPよりも上流側が圧力の高い領域となる。一方、スロートSPよりも下流側が上流側と比較して圧力の低い領域となる。したがって、マイクロジェット噴射は、圧力の低い領域に向けて噴射される事になるので、チャンバ17内の圧力を必要以上に高めることなく、十分な流量を確保できる。そして、スロートSPの直後、つまり、スロートSPから軸方向に対して鋭角をなすように、下流方向に向けてスムーズにマイクロジェット噴射が行われる。
また、ジェットエンジン100を駆動させると各部品の温度が上昇するが、従来の配管を用いたノズルと比較してマイクロジェットリング16の熱膨張量を小さく抑えることができる。このため、マイクロジェットリング16に形成された噴射管26の直径の変化量も従来と比較して小さく、噴射管26を介して噴射される空気Aの流量が低減しにくい。
ここで、マイクロジェットリング16に形成されている噴射管26の個数を、以下の式に基づいて設定することにより、より効率よく騒音を低減することができる。
噴射管26の個数nは、
σ=d/(πD/n) ・・・(1)
0.11≦σ≦0.16・・・(2)
を満たすように設定される。
なお、設計指数σは、マイクロジェットリング16のジェット流排出口16Aの円周において、噴射管26の占める割合である。設計指数σを式(2)を満たすように設定することにより、騒音を効率よく低減することが可能になる知見が得られている。
上述の実施形態によれば、従来のように配管のノズルを用いることなく、マイクロジェットリング16に形成された複数の噴射管26を利用してジェット流とバイパス流との合流部に向けてマイクロジェットを噴射させることができる。このため、配管のノズルを用いる場合と比較して、マイクロジェット噴射部分の剛性を高めることができる。剛性を高めることができる分、噴射管26の直径を大きく設定することができ、圧力損失を低減できる。よって、マイクロジェットリング16の損傷を防止し、かつ効率よくマイクロジェット噴射させることにより効率よく騒音を低減できる。
さらに、従来の配管に代わってマイクロジェットリング16を用いているので、配管によるキャビティ流れを防止でき、付加騒音の発生を抑制できる。
しかも、マイクロジェットリング16に差込部23を一体成形し、この差込部23をチャンバ17の開口部17Aに印籠嵌合させるだけでマイクロジェットリング16の組み付けを完了させることができる。このため、ジェットエンジン100の組み立て作業性を向上させることが可能になる。
図6に示す検証は、以下の条件を用い、各々の軸方向位置における全圧損失係数を数値解析することで行なった。
流路5の内径:Φ5mm、32本
マイクロジェット出口面積:噴射管内径Φ3.15(mm)×sqrt(32本/20本)=Φ3.52mm
ここで、図6に破線で示すようにチャンバ17が設けられていない場合、図6に示す軸方向位置0.1(m)の位置における全圧損失の増加と同様に、流路5とチャンバ17の接続位置である軸方向位置―0.18(m)の位置から全圧損失が急激に増加する。軸方向位置―0.18(m)の位置から、軸方向位置0.1(m)の位置と同様に全圧損失が増加すると、噴射管26の出口における全圧損失は50(%)を超えることが明らかである。
このように、本実施の形態に係る騒音低減装置においては、チャンバ17が備えられているため、マイクロジェットを噴射するためのエンジンからの抽気圧力の損失を大きく低減させ、コンプレッサからの多大な抽気を必要としないという効果が得られる。
例えば、上述の実施形態では、マイクロジェットリング16の基端に差込部23を一体成形し、この差込部23の内周面と外周面とにそれぞれOリング25を装着してチャンバ17の開口部17Aに印籠嵌合する場合について説明した。しかしながら、これに限られるものではなく、以下の図7に示す構成により、マイクロジェットリング16とチャンバ17とを接続してもよい。
図7に示すように、チャンバ17の内周壁部18、および外周壁部22には、開口部17A側にそれぞれ段差により薄肉形成された段差面28,29が形成されている。一方、マイクロジェットリング16に一体成形されている差込部23は、段差面28,29に対応するように形成され、この段差面28,29に嵌合可能になっている。
なお、シール部材31を耐熱合金を用いたメタルシールとすることにより、シール部材31の耐熱温度を約800℃程度に設定することが可能になる。シール部材31としては、Cリング、Eリング、およびUリング等を用いることが可能である。
図8に示すように、チャンバ17の内周壁部18の下流側端(図8における右側端)には、マイクロジェットリング16の内周面16a側が一体成形されている。これにより、マイクロジェットリング16と、チャンバ17の内周壁部18、および外フランジ部18aとによって凹部35が全周に亘って形成される。この凹部35をチャンバ17の外周壁部22によって閉塞する。
これにより、マイクロジェットリング16とチャンバ17との接合部のシール性を確保することができる。
この場合、マイクロジェットリング16を分割することにより形成される各リング片(不図示)の合わせ面に、シール部材等を用いて気密性を確保する。また、各リング片に、それぞれ噴射管26を形成してもよいし、各リング片の合わせ面に溝を形成し、この溝を重ね合わせることで噴射管26を構成するようにしてもよい。
また、本発明に係る騒音低減装置によれば、組み立て作業性を向上でき、騒音低減効果を確実に得ることが可能である。
2 ケーシング
3 筒状隔壁(主ノズル)
3A 噴出側周縁
4 圧縮機
5 流路
12 燃焼器
16 マイクロジェットリング
16A ジェット流排出口
17 チャンバ
20 供給路
26 噴射管
26a 第一管
26b 第二管
27 弧状面部
100 ジェットエンジン
A 空気
X ジェット流
Claims (4)
- ジェットエンジンの主ノズルの噴出側周縁に、周方向に等間隔に形成された複数の噴射管を有するマイクロジェットリングを設け、
前記ジェットエンジン内の燃焼器より上流側の流路から圧縮空気の一部を取り入れて前記複数の噴射管まで導く供給路を設け、
前記複数の噴射管は、前記圧縮空気の一部を、前記主ノズルから噴出されるジェット流に向けて噴射させる騒音低減装置。 - 前記マイクロジェットリングを前記ジェット流の上流側から下流側に向かうに従って縮径するように形成すると共に、
前記マイクロジェットリングの吐出側周縁に、このマイクロジェットリングの内周面が先端に向かうに従って拡径するように弧状面部を全周に亘って形成した請求項1に記載の騒音低減装置。 - 前記複数の噴射管の少なくとも噴出口側近傍が前記主ノズルの軸方向に対して鋭角をなすように、下流方向に向けて形成されている請求項1又は請求項2に記載の騒音低減装置。
- 前記マイクロジェットリングと前記流路との間に、これらマイクロジェットリングと流路とを連通するチャンバを設けた請求項1~請求項3の何れかに記載の騒音低減装置。
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US13/504,195 US9528468B2 (en) | 2009-10-28 | 2010-10-26 | Noise reduction system |
CA2779050A CA2779050C (en) | 2009-10-28 | 2010-10-26 | Noise reduction system |
JP2011538427A JP5459317B2 (ja) | 2009-10-28 | 2010-10-26 | 騒音低減装置 |
EP10826698.2A EP2495423B1 (en) | 2009-10-28 | 2010-10-26 | Noise reduction device |
CN201080048444.2A CN102597474B (zh) | 2009-10-28 | 2010-10-26 | 噪声降低装置 |
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CN103133180A (zh) * | 2011-11-25 | 2013-06-05 | 中航商用航空发动机有限责任公司 | 一种低喷流噪声喷管及包含该喷管的涡扇发动机 |
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FR3009027B1 (fr) * | 2013-07-26 | 2018-04-06 | Airbus Operations | Ensemble turbomachine d'aeronef a bruit de jet attenue. |
CN114687887A (zh) * | 2015-03-26 | 2022-07-01 | 赛峰飞机发动机公司 | 具有用于微射流的格栅以降低涡轮发动机的喷射噪声的装置 |
CN113107705B (zh) * | 2021-04-08 | 2022-09-27 | 西北工业大学 | 一种带红外抑制措施的双s弯收扩喷管 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2990905A (en) * | 1957-05-13 | 1961-07-04 | Lilley Geoffrey Michael | Jet noise suppression means |
JP2005195019A (ja) | 2003-12-30 | 2005-07-21 | General Electric Co <Ge> | 振動ジェットを使用してジェットエンジン排気騒音を低減するための装置 |
US7246481B2 (en) | 2004-03-26 | 2007-07-24 | General Electric Company | Methods and apparatus for operating gas turbine engines |
JP2009247779A (ja) | 2008-04-10 | 2009-10-29 | Kowa Co | 眼光刺激装置 |
JP2010518323A (ja) | 2007-02-14 | 2010-05-27 | ザ・ボーイング・カンパニー | ジェットエンジンの排気騒音を削減するシステム及び方法 |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1515198A (fr) * | 1967-01-18 | 1968-03-01 | Snecma | Silencieux à jets fluides pour systèmes d'éjection |
US7412832B2 (en) * | 2004-03-26 | 2008-08-19 | General Electric Company | Method and apparatus for operating gas turbine engines |
FR2904663B1 (fr) * | 2006-08-01 | 2012-02-03 | Snecma | Turbomachine a double flux a variation artificielle de sa section de col |
EP2256327B1 (en) * | 2008-02-25 | 2019-09-04 | IHI Corporation | Noise reducing device, and jet propulsion system |
-
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Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2990905A (en) * | 1957-05-13 | 1961-07-04 | Lilley Geoffrey Michael | Jet noise suppression means |
JP2005195019A (ja) | 2003-12-30 | 2005-07-21 | General Electric Co <Ge> | 振動ジェットを使用してジェットエンジン排気騒音を低減するための装置 |
US7246481B2 (en) | 2004-03-26 | 2007-07-24 | General Electric Company | Methods and apparatus for operating gas turbine engines |
JP2010518323A (ja) | 2007-02-14 | 2010-05-27 | ザ・ボーイング・カンパニー | ジェットエンジンの排気騒音を削減するシステム及び方法 |
JP2009247779A (ja) | 2008-04-10 | 2009-10-29 | Kowa Co | 眼光刺激装置 |
Non-Patent Citations (1)
Title |
---|
See also references of EP2495423A4 |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103133180A (zh) * | 2011-11-25 | 2013-06-05 | 中航商用航空发动机有限责任公司 | 一种低喷流噪声喷管及包含该喷管的涡扇发动机 |
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JP5459317B2 (ja) | 2014-04-02 |
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EP2495423A4 (en) | 2015-04-15 |
EP2495423A1 (en) | 2012-09-05 |
CN102597474B (zh) | 2015-08-19 |
CA2779050C (en) | 2014-10-07 |
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JPWO2011052566A1 (ja) | 2013-03-21 |
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