US20180187598A1 - Low noise aeroengine inlet system - Google Patents
Low noise aeroengine inlet system Download PDFInfo
- Publication number
- US20180187598A1 US20180187598A1 US15/908,226 US201815908226A US2018187598A1 US 20180187598 A1 US20180187598 A1 US 20180187598A1 US 201815908226 A US201815908226 A US 201815908226A US 2018187598 A1 US2018187598 A1 US 2018187598A1
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- United States
- Prior art keywords
- splitter
- inlet duct
- compressor
- inlet
- walls
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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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
Definitions
- the described subject matter relates generally to gas turbine engines, and more particularly to controlling noise in aircraft.
- a compressor inlet system for an aeroengine comprising an inlet duct for directing an air flow to a compressor of the aeroengine, and an inlet splitter moveable between a stowed position in which the splitter is disposed substantially out of the air flow so that the inlet duct provides substantially only one passage to the compressor, and a deployed position in which the splitter is disposed in the inlet duct to divide the inlet duct into at least two passages to the compressor, and wherein at least one surface of the splitter exposed to the air flow includes an acoustic treatment configured to reduce aeroengine noise, the splitter acoustic treatment is tuned substantially for attenuating a first noise frequency and an inner surface of the inlet duct comprises at least one acoustic treatment area tuned substantially for attenuating a second noise frequency different from the first noise frequency.
- a compressor inlet system for an aeroengine comprising an inlet duct for directing an air flow to a compressor of the aeroengine, and an inlet splitter moveable between a stowed position in which the splitter is disposed substantially out of the air flow so that the inlet duct provides substantially only one passage to the compressor, and a deployed position in which the splitter is disposed in the inlet duct to divide the inlet duct into at least two passages to the compressor, and wherein at least one surface of the splitter exposed to the air flow includes an acoustic treatment configured to reduce aeroengine noise and tuned substantially for attenuating a first noise frequency, and an inner surface of the inlet duct comprises at least one acoustic treatment area tuned substantially for attenuating a second noise frequency different from the first noise frequency, wherein the at least one acoustic treatment area of the inner surface of the inlet duct is covered by the splitter when the splitter is in the stowed position and is exposed
- FIG. 1 is a schematic cross-sectional view of a turboprop aeroengine as an example illustrating application of the described subject matter
- FIG. 2 is a schematic partial perspective view of the turboprop aeroengine of FIG. 1 , illustrating an inlet system having splitter plates in a stowed position in an inlet duct;
- FIG. 3 is a schematic partial perspective view of the turboprop aeroengine of FIG. 1 , illustrating the inlet system having splitter plates in a deployed position in an inlet duct;
- FIG. 4 is a schematic front elevational view of the inlet duct of FIG. 3 showing the splitter plates in the deployed position forming two partition walls which divide a single air passage defined within a section of the inlet duct, into three air passages extending through the section of the inlet duct;
- FIG. 5 is a schematic front elevational view of the inlet duct of FIG. 2 according to another embodiment.
- FIG. 6 is a schematic top plan view of a splitter plate having perforations or noise absorption material to form an acoustic treatment area thereon.
- FIG. 1 illustrates a turboprop aeroengine as an example of the application of the described subject matter, which generally includes in serial flow communication (indicated by arrows) a compressor section 12 for pressurizing air, a combustor 14 in which the pressurized air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 16 for extracting energy from the combustion gases to drive the compressor rotors in the compressor section 12 and further drive a propeller 18 through a reduction gear box 20 .
- downstream and upstream are defined with respect to the direction of the air flow entering into and passing through the engine, indicated by arrows.
- the turboprop aeroengine may provide an inlet system 22 having an inlet duct 24 for directing the airflow indicated by the arrows, from an inlet opening 26 to a first compressor rotor (not numbered) of the compressor section 12 .
- the inlet duct 24 may have an upstream portion 28 (intake portion) and a downstream portion 30 (engine inlet portion) which is annular around the power shaft (not numbered) of the engine to direct the air flow in an annular stream toward the first compressor rotor of the compressor section 12 .
- the upstream portion 28 of the inlet duct 24 may be defined with a peripheral wall (not numbered), having opposed and substantially parallel top and bottom walls 32 , 34 with curved or rounded side walls 38 , 40 (see FIGS. 4 and 5 ).
- side walls 38 , 40 may be flat and the upstream portion 28 may define a rectangular cross-section.
- An inlet splitter apparatus (not numbered) may be provided in the inlet system 22 and may be disposed within a section 44 (see FIG. 1 ) of the upstream portion 28 of the inlet duct 24 .
- the section 44 in FIG. 1 is disposed adjacent the inlet opening 26 , but may be disposed in other locations within the upstream portion 28 of the inlet duct 24 .
- One or more acoustic treatment areas 42 may be provided on an inner surface of the inlet duct 24 which is in the section 44 as shown in FIG. 1 , but may be located in other locations within the upstream portion 28 of the inlet duct 24 .
- the inlet splitter apparatus may include four splitter plates (or may include at least one plate, as indicated in FIGS. 5 ) 46 , 48 , 50 and 52 operatively mounted within the section 44 of the inlet duct 24 .
- the splitter plates 46 and 50 may be pivotally mounted to the top wall 32 about respective pivotal axes 46 a and 50 a which are substantially parallel to a direction of the air flow as indicated by the arrow
- the splitter plates 48 and 52 may be pivotally mounted to the bottom wall 34 about respective pivotal axes 48 a and 52 a which are substantially parallel to the direction of the airflow as indicated by the arrow.
- the splitter apparatus may be operative between a stowed position as shown in FIG.
- the splitter plates 46 and 50 may be pivoted to a position parallel to and adjacent the top wall 32 and the splitter plates 48 and 52 may be pivoted to a position parallel to and adjacent the bottom wall 34 .
- the splitter plates 46 and 48 may be pivoted to extend from the respective top and bottom walls 32 , 34 into the section 44 of the inlet duct 24 to in combination form a first partition wall (not numbered) extending through the section 44 of the inlet duct 24 and the splitter plates 50 and 52 may be pivoted to extend from the respective top and bottom walls 32 , 34 into the section 44 of the inlet duct 24 to in combination form a second partition wall (not numbered) extending through the section 44 of the inlet duct 24 .
- section 44 of the inlet duct 24 is configured as substantially a single passage extending through the section 44 of the inlet duct 24 as shown in FIG. 3 .
- the splitter plates extend transversely into the inlet duct 24 in the deployed position, the single passage defined by section 44 of the inlet duct 24 is divided into three separate passages by the two partition walls extending through the section 44 of the inlet duct 24 , as shown in FIG. 4 .
- the length/diameter ratio of the section 44 of the inlet duct 24 increases to thereby improve attenuation of the noise propagation from the compressor section 12 forwards to the inlet opening 26 .
- An actuation system 54 may be provided to actuate the respective splitter plates 46 , 48 , 50 , 52 in their pivotal motion between the stowed and deployed positions as shown in FIG. 4 .
- the actuation system 54 may be electric, hydraulic or pneumatic using auxiliary power extracted from the engine or any other aircraft power source.
- a hydraulic cylinder 56 as an actuator is shown in FIG. 5 .
- the actuation system 54 moves the respective splitter plates 46 , 48 , 50 , 52 in unison to effectively create two partition walls in the inlet duct when deployed.
- the system may be periodically and partially cycled by the actuators to crack the ice.
- splitter plates may be pivotally mounted to the respective top and bottom walls of the inlet duct to operatively form one partition wall in the deployed position.
- the number of the splitter plates may also be reduced to one in another embodiment as shown in FIG. 5 .
- the only one splitter plate 36 may be pivotally mounted to the peripheral wall of the inlet duct, such as to either one of the top and bottom walls 32 , 34 (an arrow in broken lines indicates the pivotal motion).
- the splitter plate may be substantially rectangular as shown in FIG. 6 and may have a width (from the edge which is pivotally connected to one of the top and bottom walls to an opposite free edge) substantially equal to a distance measured from the top wall 32 to the bottom wall 34 , thereby forming a partition wall to separate section 44 of the inlet duct 24 , into two separate passages extending through the section 44 .
- the pivotal axes 46 a and 50 a are spaced apart by a distance to allow free pivotal motion of the respective splitter plates 46 and 50 and the pivotal axes 48 a and 52 a are spaced apart by, for example the same distance to allow free pivotal motion of the respective splitter plates 48 and 52 .
- the splitter plates may have identical shapes such as rectangular.
- a length dimension of the splitter plates may be determined by the length of the section 44 of the inlet duct 24 to be equipped with the inlet splitter apparatus.
- the width dimension of the splitter plates may be determined by the cross-sectional dimension of the section 44 of the inlet duct 24 such that the partition walls formed by the splitter plates in the deployed position, can be formed without significant gaps between adjacent splitter plates.
- the acoustic treatment area 42 defined on the inner surface of the inlet duct 24 may absorb acoustic energy when exposed to noise propagation through the inlet duct 24 .
- the total area of acoustic treatment surfaces within the inlet duct 24 may increase when the splitter apparatus is deployed in the inlet duct 24 .
- the splitter plates 46 , 48 , 50 and 52 may define an acoustic treatment area at one or both sides thereof by having acoustic treatment material applied thereto or by having perforations extending through one side to the other side thereof, as shown in FIG. 6 .
- the additional acoustic treatment areas defined on the one or both sides of the respective splitter plates are exposed to noise propagation through the inlet duct 24 , thereby improving noise attenuation.
- additional acoustic treatment may also be provided by the treatment area 42 in the inlet duct 24 which is covered by splitter plates in the stowed position but is exposed when the splitter plates are in the deployed position.
- the additional acoustic treatment areas defined on one or both sides of the splitter plates in the deployed position may be tuned to attenuate a first dominant noise frequency which is different from a second dominant noise frequency.
- the acoustic treatment area 42 affixed on the inner surface of the peripheral wall of the inlet duct 24 may be tuned to substantially attenuate the second dominant noise frequency.
Abstract
Description
- This application is a division of U.S. application Ser. No. 14/463,031 filed Aug. 19, 2014, the entire contents of which are incorporated by reference herein.
- The described subject matter relates generally to gas turbine engines, and more particularly to controlling noise in aircraft.
- Future turboprop aircraft will be larger, heavier and with more powerful engines. Traditionally the aircraft engine industry has pointed to the propellers as the dominant noise source, but with modern electronic propeller control strategies, propeller contribution to the total noise of the engine is reduced and compressor noise propagating from the engine intake can become the dominant source of noise. This is particularly true during the approach phase of flight just before landing. At approach conditions the performance of the engine inlet is less important than in other flight phases since the engine operates at lower power and the conditions are not maintained for long enough to be significant for block fuel burn. Consequently, the industry has made a great effort to improve inlet noise attenuation capabilities, particularly under flight approach conditions.
- Accordingly, there is a need to provide an improved engine inlet system for aircraft gas turbine engines.
- In one aspect, there is provided a compressor inlet system for an aeroengine, the compressor inlet system comprising an inlet duct for directing an air flow to a compressor of the aeroengine, and an inlet splitter moveable between a stowed position in which the splitter is disposed substantially out of the air flow so that the inlet duct provides substantially only one passage to the compressor, and a deployed position in which the splitter is disposed in the inlet duct to divide the inlet duct into at least two passages to the compressor, and wherein at least one surface of the splitter exposed to the air flow includes an acoustic treatment configured to reduce aeroengine noise, the splitter acoustic treatment is tuned substantially for attenuating a first noise frequency and an inner surface of the inlet duct comprises at least one acoustic treatment area tuned substantially for attenuating a second noise frequency different from the first noise frequency.
- In another aspect, there is provided a compressor inlet system for an aeroengine, the compressor inlet system comprising an inlet duct for directing an air flow to a compressor of the aeroengine, and an inlet splitter moveable between a stowed position in which the splitter is disposed substantially out of the air flow so that the inlet duct provides substantially only one passage to the compressor, and a deployed position in which the splitter is disposed in the inlet duct to divide the inlet duct into at least two passages to the compressor, and wherein at least one surface of the splitter exposed to the air flow includes an acoustic treatment configured to reduce aeroengine noise and tuned substantially for attenuating a first noise frequency, and an inner surface of the inlet duct comprises at least one acoustic treatment area tuned substantially for attenuating a second noise frequency different from the first noise frequency, wherein the at least one acoustic treatment area of the inner surface of the inlet duct is covered by the splitter when the splitter is in the stowed position and is exposed when the splitter is in the deployed position.
- Further details and other aspects of the described subject matter will be apparent from the detailed description and drawings included below.
- Reference is now made to the accompanying figures in which:
-
FIG. 1 is a schematic cross-sectional view of a turboprop aeroengine as an example illustrating application of the described subject matter; -
FIG. 2 is a schematic partial perspective view of the turboprop aeroengine ofFIG. 1 , illustrating an inlet system having splitter plates in a stowed position in an inlet duct; -
FIG. 3 is a schematic partial perspective view of the turboprop aeroengine ofFIG. 1 , illustrating the inlet system having splitter plates in a deployed position in an inlet duct; -
FIG. 4 is a schematic front elevational view of the inlet duct ofFIG. 3 showing the splitter plates in the deployed position forming two partition walls which divide a single air passage defined within a section of the inlet duct, into three air passages extending through the section of the inlet duct; -
FIG. 5 is a schematic front elevational view of the inlet duct ofFIG. 2 according to another embodiment; and -
FIG. 6 is a schematic top plan view of a splitter plate having perforations or noise absorption material to form an acoustic treatment area thereon. - It will be noted that throughout the appended drawings, like features are identified by like reference numerals.
-
FIG. 1 illustrates a turboprop aeroengine as an example of the application of the described subject matter, which generally includes in serial flow communication (indicated by arrows) acompressor section 12 for pressurizing air, acombustor 14 in which the pressurized air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and aturbine section 16 for extracting energy from the combustion gases to drive the compressor rotors in thecompressor section 12 and further drive apropeller 18 through areduction gear box 20. - It should be noted that the terms downstream and upstream are defined with respect to the direction of the air flow entering into and passing through the engine, indicated by arrows.
- In this example, the turboprop aeroengine may provide an
inlet system 22 having aninlet duct 24 for directing the airflow indicated by the arrows, from an inlet opening 26 to a first compressor rotor (not numbered) of thecompressor section 12. Theinlet duct 24 according to one embodiment, may have an upstream portion 28 (intake portion) and a downstream portion 30 (engine inlet portion) which is annular around the power shaft (not numbered) of the engine to direct the air flow in an annular stream toward the first compressor rotor of thecompressor section 12. - Referring to
FIGS. 1-6 and according to one embodiment, theupstream portion 28 of theinlet duct 24 may be defined with a peripheral wall (not numbered), having opposed and substantially parallel top andbottom walls rounded side walls 38, 40 (seeFIGS. 4 and 5 ). Alternatively,side walls upstream portion 28 may define a rectangular cross-section. An inlet splitter apparatus (not numbered) may be provided in theinlet system 22 and may be disposed within a section 44 (seeFIG. 1 ) of theupstream portion 28 of theinlet duct 24. Thesection 44 inFIG. 1 is disposed adjacent the inlet opening 26, but may be disposed in other locations within theupstream portion 28 of theinlet duct 24. - One or more
acoustic treatment areas 42 may be provided on an inner surface of theinlet duct 24 which is in thesection 44 as shown inFIG. 1 , but may be located in other locations within theupstream portion 28 of theinlet duct 24. - The inlet splitter apparatus according to one embodiment may include four splitter plates (or may include at least one plate, as indicated in
FIGS. 5 ) 46, 48, 50 and 52 operatively mounted within thesection 44 of theinlet duct 24. For example, thesplitter plates top wall 32 about respectivepivotal axes splitter plates bottom wall 34 about respectivepivotal axes FIG. 2 and a deployed position as shown inFIG. 3 . In the stowed position, thesplitter plates top wall 32 and thesplitter plates bottom wall 34. In the deployed position, thesplitter plates bottom walls section 44 of theinlet duct 24 to in combination form a first partition wall (not numbered) extending through thesection 44 of theinlet duct 24 and thesplitter plates bottom walls section 44 of theinlet duct 24 to in combination form a second partition wall (not numbered) extending through thesection 44 of theinlet duct 24. - As illustrated in
FIG. 2 , when the splitter plates are positioned parallel to and adjacent the respective top andbottom walls inlet duct 24 in the stowed position,section 44 of theinlet duct 24 is configured as substantially a single passage extending through thesection 44 of theinlet duct 24 as shown inFIG. 3 . When the splitter plates extend transversely into theinlet duct 24 in the deployed position, the single passage defined bysection 44 of theinlet duct 24 is divided into three separate passages by the two partition walls extending through thesection 44 of theinlet duct 24, as shown inFIG. 4 . - It is understood that when the inlet splitter apparatus changes from the stowed position to the deployed position, the length/diameter ratio of the
section 44 of theinlet duct 24 increases to thereby improve attenuation of the noise propagation from thecompressor section 12 forwards to the inlet opening 26. - An
actuation system 54 according to one embodiment may be provided to actuate therespective splitter plates FIG. 4 . Theactuation system 54 may be electric, hydraulic or pneumatic using auxiliary power extracted from the engine or any other aircraft power source. Ahydraulic cylinder 56 as an actuator is shown inFIG. 5 . Like the reduced requirement for inlet performance during aircraft landing approach flight, such extraction of auxiliary power from the engine is not limiting power or is not sustained for a long enough duration to be a block fuel driver. Theactuation system 54 moves therespective splitter plates - In icing conditions the system may be periodically and partially cycled by the actuators to crack the ice.
- Depending on inlet geometry, other configurations can be conceived with different numbers of splitters as required to optimize the balance between cost, weight and noise attenuation capabilities. For example, two splitter plates may be pivotally mounted to the respective top and bottom walls of the inlet duct to operatively form one partition wall in the deployed position.
- The number of the splitter plates may also be reduced to one in another embodiment as shown in
FIG. 5 . The only onesplitter plate 36 may be pivotally mounted to the peripheral wall of the inlet duct, such as to either one of the top andbottom walls 32, 34 (an arrow in broken lines indicates the pivotal motion). When only onesplitter plate 36 is provided, the splitter plate may be substantially rectangular as shown inFIG. 6 and may have a width (from the edge which is pivotally connected to one of the top and bottom walls to an opposite free edge) substantially equal to a distance measured from thetop wall 32 to thebottom wall 34, thereby forming a partition wall toseparate section 44 of theinlet duct 24, into two separate passages extending through thesection 44. - As illustrated in
FIGS. 2-3 , it is understood that thepivotal axes respective splitter plates pivotal axes respective splitter plates section 44 of theinlet duct 24 to be equipped with the inlet splitter apparatus. The width dimension of the splitter plates may be determined by the cross-sectional dimension of thesection 44 of theinlet duct 24 such that the partition walls formed by the splitter plates in the deployed position, can be formed without significant gaps between adjacent splitter plates. - The
acoustic treatment area 42 defined on the inner surface of theinlet duct 24 may absorb acoustic energy when exposed to noise propagation through theinlet duct 24. In order to improve the absorption of acoustic energy, the total area of acoustic treatment surfaces within theinlet duct 24 may increase when the splitter apparatus is deployed in theinlet duct 24. For example, thesplitter plates FIG. 6 . In the deployed position, the additional acoustic treatment areas defined on the one or both sides of the respective splitter plates are exposed to noise propagation through theinlet duct 24, thereby improving noise attenuation. Furthermore, additional acoustic treatment may also be provided by thetreatment area 42 in theinlet duct 24 which is covered by splitter plates in the stowed position but is exposed when the splitter plates are in the deployed position. - The additional acoustic treatment areas defined on one or both sides of the splitter plates in the deployed position, may be tuned to attenuate a first dominant noise frequency which is different from a second dominant noise frequency. The
acoustic treatment area 42 affixed on the inner surface of the peripheral wall of theinlet duct 24 may be tuned to substantially attenuate the second dominant noise frequency. - The above description is meant to be exemplary only, and one skilled in the art will recognize that changes may be made to the embodiments described without departing from the scope of the described subject matter. For example, the described subject matter may be applicable to any suitable engine, such as aeroengines configured differently from the turboprop aeroengine as illustrated in the drawings. For example, it may be suitable to provide in a turboshaft (helicopter), turbofan, or other gas turbine or other type of aeroengine. Still other modifications which fall within the scope of the described subject matter will be apparent to those skilled in the art, in light of a review of this disclosure, and such modifications are intended to fall within the appended claims.
Claims (15)
Priority Applications (1)
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US15/908,226 US20180187598A1 (en) | 2014-08-19 | 2018-02-28 | Low noise aeroengine inlet system |
Applications Claiming Priority (2)
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US14/463,031 US9957889B2 (en) | 2014-08-19 | 2014-08-19 | Low noise aeroengine inlet system |
US15/908,226 US20180187598A1 (en) | 2014-08-19 | 2018-02-28 | Low noise aeroengine inlet system |
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US14/463,031 Division US9957889B2 (en) | 2014-08-19 | 2014-08-19 | Low noise aeroengine inlet system |
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US20180187598A1 true US20180187598A1 (en) | 2018-07-05 |
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US14/463,031 Active 2036-10-12 US9957889B2 (en) | 2014-08-19 | 2014-08-19 | Low noise aeroengine inlet system |
US15/908,226 Abandoned US20180187598A1 (en) | 2014-08-19 | 2018-02-28 | Low noise aeroengine inlet system |
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US9957889B2 (en) * | 2014-08-19 | 2018-05-01 | Pratt & Whitney Canada Corp. | Low noise aeroengine inlet system |
US11098650B2 (en) | 2018-08-10 | 2021-08-24 | Pratt & Whitney Canada Corp. | Compressor diffuser with diffuser pipes having aero-dampers |
US10823196B2 (en) | 2018-08-10 | 2020-11-03 | Pratt & Whitney Canada Corp. | Compressor diffuser with diffuser pipes varying in natural vibration frequencies |
CN112879162B (en) * | 2021-01-19 | 2021-12-14 | 南京航空航天大学 | S bending offset adjustable aircraft engine air inlet duct |
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- 2015-08-19 PL PL15181596.6T patent/PL2987988T3/en unknown
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2018
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Also Published As
Publication number | Publication date |
---|---|
US20160053684A1 (en) | 2016-02-25 |
CA2900388A1 (en) | 2016-02-19 |
US9957889B2 (en) | 2018-05-01 |
EP2987988A1 (en) | 2016-02-24 |
PL2987988T3 (en) | 2022-08-08 |
EP2987988B1 (en) | 2022-03-23 |
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