US3270953A - Axial flow compressor, blower or ventilator with reduced noise production - Google Patents

Axial flow compressor, blower or ventilator with reduced noise production Download PDF

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US3270953A
US3270953A US368649A US36864964A US3270953A US 3270953 A US3270953 A US 3270953A US 368649 A US368649 A US 368649A US 36864964 A US36864964 A US 36864964A US 3270953 A US3270953 A US 3270953A
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blade
blades
axis
leading edge
trailing
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US368649A
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Jerie Jan
Nemec Jaroslav
Moravec Zdenek
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/002—Axial flow fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • This invention relates to a blade arrangement in axialflow compressors, blowers, or ventilators which reduces the operating noise of these machines.
  • Axial-flow compressors and similar machines generate a so-called siren noise which is very unpleasant and may prevent their application in spite of their known advantages.
  • the siren noise originates in the blading of conventional compressors, blowers or ventilators.
  • the invention provides two solutions of the noisiness problem in axial-flow compressors and like machines which may be applied simultaneously or separately.
  • the operating noise of these machines is reduced by using a specific ratio of the number of rotor blades to the number of stator blades, and by selecting angular relationships of the edges of the rotor and stator blades which will be explained below in more detail.
  • Each of these two noise reducing measures may be used separately or with the other one.
  • the numerical ratio of the rotor blades to the stator blades in accordance with this invention is either 1 i ZIC 2 wherein Z and Z respectively are the numbers of stator and rotor blades, 1' is a positive, odd, integral number, and k is a positive, integral number; or
  • FIGS. 1, 2, .3, are illustrative of conditions in the case of crossing of a stator blade by a rotor blade
  • FIGS. 4 and 5 for a crossing of a rotor blade by a stator blade.
  • FIG. 1 there is shown a stator blade in airfoil section on a cylindrical surface of diameter D about the machine axis and developed in a plane.
  • the mean or camber line H of the section is the locus of the centers of circles K inscribed into the contour of the blade profile.
  • the points of intersection of the camber line H with the leading and trailing edges are at A and B respectively.
  • the length of the chord between points A and B is C. Normal lines are drawn on the chord AB at the distance C/4 from the points A and B respectively, and their intersections with the mean line H are determined.
  • Lines connecting the points of intersection with the points A, B respectively and extending outward through the last-mentioned points constitute a leading ray or line a and a trailing ray or line b.
  • the function of these rays or lines will become presently apparent.
  • the direction of these rays is important in determining the blade cross-over.
  • FIGS. 2 and 3 illustrate the crossing of a stator blade by the leading edge of a rotor blade.
  • the stator 1 is arranged ahead of the rotor 2 in the direction of fluid flow as indicated by arrows.
  • FIG. 2 shows blades in section on a cylindrical surface of diameter D and developed in a plane.
  • the trailing edge 3 of the stator 1 includes the points B of all cylindrical sections.
  • the leading edge 4 of the rotor blade 2 includes the corresponding points A.
  • the edge 4 generates a surface of rota-tion while rotating about the axis 0 of the rotor.
  • the trailing ray b of the stator blade 1 on the selected diameter D intersects the surface of rotation at B.
  • the line connecting points of the surface of rotation analogous to B is projected axially on a plane perpendicular to the axis 0 and defines a projected line 3, as shown in FIG. 3.
  • the leading edge 4 of the rotor blade 2 is projected in a similar manner on the perpendicular plane, whereby a line 4 is defined.
  • FIG. 4 shows a rotor blade 5, a stator blade 6, the trailing edge 7 of the rotor blade 5, and the leading edge 8 of the stator blade 6. Projected lines 7', 8' are derived from the edges 7, 8 in a manner evident from the above description of FIGS. 2 and 3.
  • the value 1- is obtained from FIGS. 4 and 5 by the same method as described above.
  • each set being spaced about a common axis and extending radially between a root circle near said axis and a tip circle remote from said axis, said circles being centered in said axis, said pitch being the circumferential spacing of adjacent blades of the other set as measured on said tip circle,
  • said characteristic crossing value being the circumferential spacing of two lines projected on a plane perpendicular to said axis, said spacing being measured on said tip circle, said projected lines intersecting in said root circle,
  • one of said projected lines being an axial projection of a line of intersection between a surface of rotation about said axis and a plurality of radially spaced trailing rays of one of the blades of said other set, each trailing ray being defined by the point of intersection of the camber line of said one blade with the trailing edge of said one blade in the airfoil section of said one blade and by a point on said camber line spaced from said trailing edge toward the leading edge of said one blade .a distance equal to one fourth of the length of the chord between said camber line and said leading edge, said distance being measured along said chord,
  • said surface of rotation being defined by said leading edge of the last-mentioned blade when said other set rotates about said axis.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Sept. 6, 1966 J. JERIE ETAL 3,
AXIAL FLOW COMPRESSQR, BLOWER OR VENTILATOR WITH EDUCE OISE UCTION R D N PROD Filed May 19, 1964 INVENTORS 75m Tar/e, Jaraa/ar mec Qden k /arazrec Maud/ 4W United States Patent 3,270,953 AXIAL FLOW COMPRESSOR, BLOWER 0R VENTI- LATOR WITH REDUCED NOISE PRODUCTION Jan Jerie, 27 Komornicka, Prague 6, Czechoslovak a; Jaroslav Nmec, 3 Libicka, Prague 3, Czechoslovakia; and Zdenk Moravec, 8 Legerova, Prague 2, Czechoslovakia Filed May 19, 1964, Ser. No. 368,649 Claims priority, application Czechoslovakia, May 21, 1963, 2,900/ 63 2 Claims. (Cl. 230-120) This invention relates to a blade arrangement in axialflow compressors, blowers, or ventilators which reduces the operating noise of these machines.
Axial-flow compressors and similar machines generate a so-called siren noise which is very unpleasant and may prevent their application in spite of their known advantages.
The siren noise originates in the blading of conventional compressors, blowers or ventilators.
We have found by theoretical and experimental Work that the siren noise is produced when the blades pass through wakes behind the preceding blades and that the mutual position of the blades of axially adjacent rows is therefore closely related to this noise.
The invention provides two solutions of the noisiness problem in axial-flow compressors and like machines which may be applied simultaneously or separately.
In accordance with this invention, the operating noise of these machines is reduced by using a specific ratio of the number of rotor blades to the number of stator blades, and by selecting angular relationships of the edges of the rotor and stator blades which will be explained below in more detail. Each of these two noise reducing measures may be used separately or with the other one.
The numerical ratio of the rotor blades to the stator blades in accordance with this invention is either 1 i ZIC 2 wherein Z and Z respectively are the numbers of stator and rotor blades, 1' is a positive, odd, integral number, and k is a positive, integral number; or
wherein i and k are integral positive numbers.
These ratios are generally valid, and reach an optimum value when Z is smaller than Z The relative position of the leading edges and the trailing edges of the blades of two adjacent blade wheels, that is, rotor and stator or vice versa, has been found to aifect the noise level as a function of the parameter S wherein -r is the characteristic value of blade crossing of the stator and rotor wheels, or of the rotor and stator wheels, and can be determined graphically as a distance in the circle defined by the blade tips and having a diameter D and T0 is the pitch or spacing between circumferentially adjacent rotor or stator blades, also as measured on the circle of diameter D whereby For low machine noise, the parameter S should be greater than 0.65. It reaches its optimum value at S=Z,/Z
The invention will be best understood from the following description relating to the accompanying drawing which shows dimensional relationships relevant to blade crossing. FIGS. 1, 2, .3, are illustrative of conditions in the case of crossing of a stator blade by a rotor blade, and FIGS. 4 and 5 for a crossing of a rotor blade by a stator blade.
The manner of determining the characteristic crossing value 1 will now be explained in more detail.
Referring more particularly to FIG. 1, there is shown a stator blade in airfoil section on a cylindrical surface of diameter D about the machine axis and developed in a plane. The mean or camber line H of the section is the locus of the centers of circles K inscribed into the contour of the blade profile. The points of intersection of the camber line H with the leading and trailing edges are at A and B respectively. The length of the chord between points A and B is C. Normal lines are drawn on the chord AB at the distance C/4 from the points A and B respectively, and their intersections with the mean line H are determined. Lines connecting the points of intersection with the points A, B respectively and extending outward through the last-mentioned points constitute a leading ray or line a and a trailing ray or line b. The function of these rays or lines will become presently apparent.
The direction of these rays is important in determining the blade cross-over.
FIGS. 2 and 3 illustrate the crossing of a stator blade by the leading edge of a rotor blade. The stator 1 is arranged ahead of the rotor 2 in the direction of fluid flow as indicated by arrows. FIG. 2 shows blades in section on a cylindrical surface of diameter D and developed in a plane. The trailing edge 3 of the stator 1 includes the points B of all cylindrical sections. The leading edge 4 of the rotor blade 2 includes the corresponding points A. The edge 4 generates a surface of rota-tion while rotating about the axis 0 of the rotor. The trailing ray b of the stator blade 1 on the selected diameter D intersects the surface of rotation at B. The line connecting points of the surface of rotation analogous to B is projected axially on a plane perpendicular to the axis 0 and defines a projected line 3, as shown in FIG. 3. The leading edge 4 of the rotor blade 2 is projected in a similar manner on the perpendicular plane, whereby a line 4 is defined. When the lines 3' and 4' are shifted tangularly about the axis 0 by rotation of the rotor until they intersect at a point B of the circle of root diameter D the circumferential distance of the lines 3', 4', as measured on a circle of tip diameter D about the axis 0 is the characteristic crossing value.
Smil-iar considerations hold also for the crossing of a rotor blade by a stator blade, as shown in FIGS. 4 and 5. FIG. 4 shows a rotor blade 5, a stator blade 6, the trailing edge 7 of the rotor blade 5, and the leading edge 8 of the stator blade 6. Projected lines 7', 8' are derived from the edges 7, 8 in a manner evident from the above description of FIGS. 2 and 3. The value 1- is obtained from FIGS. 4 and 5 by the same method as described above.
To, as mentioned above, is the pitch or circumferential distance of adjacent blades of the rotor or stator, and the machine noise is low when and reaches a minimum at S: JZ
Experiments have shown that an axial compressor meeting the afore-described conditions of numerical blade ratio and crossing characteristics either individually or simultaneously produces noise at a level harmless from the point of view of industrial health.
What we claim is:
1. An axial compressor, blower, or ventilator having a set of rotor blades and a set of stator blades, said blades satisfying the relationship S='r/'r 0.65, wherein 1- is the characteristic crossing value of one of said sets by the other set, and To is the pitch of the blades of said other set,
(1) the blades of each set being spaced about a common axis and extending radially between a root circle near said axis and a tip circle remote from said axis, said circles being centered in said axis, said pitch being the circumferential spacing of adjacent blades of the other set as measured on said tip circle,
(2) said characteristic crossing value being the circumferential spacing of two lines projected on a plane perpendicular to said axis, said spacing being measured on said tip circle, said projected lines intersecting in said root circle,
(3) one of said projected lines being an axial projection of a line of intersection between a surface of rotation about said axis and a plurality of radially spaced trailing rays of one of the blades of said other set, each trailing ray being defined by the point of intersection of the camber line of said one blade with the trailing edge of said one blade in the airfoil section of said one blade and by a point on said camber line spaced from said trailing edge toward the leading edge of said one blade .a distance equal to one fourth of the length of the chord between said camber line and said leading edge, said distance being measured along said chord,
(4) the other one of said projected lines being an axial projection of the leading edge of one blade of the other set,
(5) said surface of rotation being defined by said leading edge of the last-mentioned blade when said other set rotates about said axis.
2. A compressor, blower, or ventilator as set forth in claim 1, wherein the ratio of the number Z of said rotor blades to the number Z of said stator blades is wherein Y is an integral positive odd number, and k is an integral positive number.
References Cited by the Examiner UNITED STATES PATENTS 1,585,218 5/1926 Watanabe -165 2,191,341 2/1940 Curley 230-12O 3,194,487 7/1965 Tyler et a1. 230-122 FOREIGN PATENTS 226,203 7/1925 Great Britain.
MARK NEWMAN, Primary Examiner. HENRY F. RADUAZO, Examiner.

Claims (1)

1. AN AXIAL COMPRESSOR, BLOWER, OR VENTILATOR HAVING A SET OF ROTOR BLADES AND A SET OF STATOR BLADES, SAID BLADES SATISFYING THE RELATIONSHIP S=$/$0>0.65, WHEREIN R IS THE CHARACTERISTIC CROSSING VALUE OF ONE OF SAID SETS BY THE OTHER SET, AND RO IS THE PITCH OF THE BLADES OF SAID OTHER SET, (1) THE BLADES OF EACH SET BEING SPACED ABOUT A COMMON AXIS AND EXTENDING RADIALLY BETWEEN A ROOT CIRCLE NEAR SAID AXIS AND A TIP CIRCLE REMOTE FROM SAID AXIS, SAID CIRCLES BEING CENTERED IN SAID AXIS, SAID PITCH BEING THE CIRCUMFERENTIAL SPACING OF ADJACENT BLADES OF THE OTHER SET AS MEASURED ON SAID TIP CIRCLE, (2) SAID CHARACTERISTIC CROSSING VALUE BEING THE CIRCUMFERENTIAL SPACING OF TWO LINES PROJECTED ON A PLANE PERPENDICULAR TO SAID AXIS, SAID SPACING BEING MEASURED ON SAID TIP CIRCLE, SAID PROJECTED LINES INTERSECTING IN SAID ROOT CIRCLE, (3) ONE OF SAID PROJECTED LINES BEING AN AXIAL PROJECTION OF A LINE OF INTERSECTION BETWEEN A SURFACE OF ROTATION ABOUT SAID AXIS AND A PLURALITY OF RADIALLY SPACED TRAILING RAYS OF ONE OF THE BLADES OF SAID OTHER SET, EACH TRAILING RAY BEING DEFINED BY THE POINT OF INTERSECTION OF THE CHAMBER LINE OF SAID ONE BLADE WITH THE TRAILING EDGE OF SAID ONE BLADE IN THE AIRFOIL SECTION OF SAID ONE BLADE AND BY A POINT ON SAID CAMBER LINE SPACED FROM SAID TRAILING EDGE TOWARD THE LEADING EDGE OF SAID ONE BLADE A DISTANCE EQUAL TO ONE FOURTH OF THE LENGTH OF THE CHORD BETWEEN SAID CAMBER LINE AND SAID LEADING EDGE, SAID DISTANCE BEING MEASURED ALONG SAID CHORD, (4) THE OTHER ONE OF SAID PROJECTED LINES BEING AN AXIAL PROJECTION OF THE LEADING EDGE OF ONE BLADE OF THE OTHER SET, (5) SAID SURFACE OF ROTATION BEING DEFINED BY SAID LEADING EDGE OF THE LAST-MENTIONED BLADE WHEN SAID OTHER SET ROTATES ABOUT SAID AXIS.
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Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3574477A (en) * 1969-02-19 1971-04-13 Boeing Co Noise attenuating system for rotary engines
US3764225A (en) * 1970-05-27 1973-10-09 Bbc Brown Boveri & Cie Technique and blade arrangement to reduce the serpentine motion of a mass particle flowing through a turbomachine
US4046489A (en) * 1975-10-08 1977-09-06 Eagle Motive Industries, Inc. Aerodynamic fan blade
US4131387A (en) * 1976-02-27 1978-12-26 General Electric Company Curved blade turbomachinery noise reduction
US4431376A (en) * 1980-10-27 1984-02-14 United Technologies Corporation Airfoil shape for arrays of airfoils
US4732532A (en) * 1979-06-16 1988-03-22 Rolls-Royce Plc Arrangement for minimizing buzz saw noise in bladed rotors
US5169288A (en) * 1991-09-06 1992-12-08 General Electric Company Low noise fan assembly
US5588618A (en) * 1994-05-04 1996-12-31 Eurocopter France Counter-torque device with rotor and flow-straightening stator, both of which are ducted, and phase modulation of the blades of the rotor, for helicopter
US5634611A (en) * 1994-05-04 1997-06-03 Eurocopter France Counter-torque device with rotor and flow straightening stator, both of which are ducted, and inclined flow-straightening vanes
US20080022691A1 (en) * 2004-04-02 2008-01-31 Mtu Aero Engines Gmbh Method for Designing a Low-Pressure Turbine of an Aircraft Engine, and Low-Pressure Turbine
US8246292B1 (en) * 2012-01-31 2012-08-21 United Technologies Corporation Low noise turbine for geared turbofan engine
US8632301B2 (en) 2012-01-31 2014-01-21 United Technologies Corporation Low noise compressor rotor for geared turbofan engine
US8714913B2 (en) 2012-01-31 2014-05-06 United Technologies Corporation Low noise compressor rotor for geared turbofan engine
US8834099B1 (en) 2012-09-28 2014-09-16 United Technoloiies Corporation Low noise compressor rotor for geared turbofan engine
US9624834B2 (en) 2012-09-28 2017-04-18 United Technologies Corporation Low noise compressor rotor for geared turbofan engine
US9650965B2 (en) 2012-09-28 2017-05-16 United Technologies Corporation Low noise compressor and turbine for geared turbofan engine
CN112228402A (en) * 2020-09-25 2021-01-15 杭州微光电子股份有限公司 Fan guiding device
US11143109B2 (en) 2013-03-14 2021-10-12 Raytheon Technologies Corporation Low noise turbine for geared gas turbine engine
US11719161B2 (en) 2013-03-14 2023-08-08 Raytheon Technologies Corporation Low noise turbine for geared gas turbine engine
US12123432B2 (en) 2012-01-31 2024-10-22 Rtx Corporation Low noise turbine for geared turbofan engine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB226203A (en) * 1923-12-10 1925-07-23 Oerlikon Maschf Improvements in stators and rotors for turbines
US1585218A (en) * 1924-03-26 1926-05-18 Watanabe Gennojo Soundless double propeller for aeroplanes
US2191341A (en) * 1937-02-26 1940-02-20 Jeffrey Mfg Co Ventilator
US3194487A (en) * 1963-06-04 1965-07-13 United Aircraft Corp Noise abatement method and apparatus

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB226203A (en) * 1923-12-10 1925-07-23 Oerlikon Maschf Improvements in stators and rotors for turbines
US1585218A (en) * 1924-03-26 1926-05-18 Watanabe Gennojo Soundless double propeller for aeroplanes
US2191341A (en) * 1937-02-26 1940-02-20 Jeffrey Mfg Co Ventilator
US3194487A (en) * 1963-06-04 1965-07-13 United Aircraft Corp Noise abatement method and apparatus

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3574477A (en) * 1969-02-19 1971-04-13 Boeing Co Noise attenuating system for rotary engines
US3764225A (en) * 1970-05-27 1973-10-09 Bbc Brown Boveri & Cie Technique and blade arrangement to reduce the serpentine motion of a mass particle flowing through a turbomachine
US4046489A (en) * 1975-10-08 1977-09-06 Eagle Motive Industries, Inc. Aerodynamic fan blade
US4131387A (en) * 1976-02-27 1978-12-26 General Electric Company Curved blade turbomachinery noise reduction
US4732532A (en) * 1979-06-16 1988-03-22 Rolls-Royce Plc Arrangement for minimizing buzz saw noise in bladed rotors
US4431376A (en) * 1980-10-27 1984-02-14 United Technologies Corporation Airfoil shape for arrays of airfoils
US5169288A (en) * 1991-09-06 1992-12-08 General Electric Company Low noise fan assembly
US5588618A (en) * 1994-05-04 1996-12-31 Eurocopter France Counter-torque device with rotor and flow-straightening stator, both of which are ducted, and phase modulation of the blades of the rotor, for helicopter
US5634611A (en) * 1994-05-04 1997-06-03 Eurocopter France Counter-torque device with rotor and flow straightening stator, both of which are ducted, and inclined flow-straightening vanes
US20080022691A1 (en) * 2004-04-02 2008-01-31 Mtu Aero Engines Gmbh Method for Designing a Low-Pressure Turbine of an Aircraft Engine, and Low-Pressure Turbine
US7806651B2 (en) 2004-04-02 2010-10-05 Mtu Aero Engines Gmbh Method for designing a low-pressure turbine of an aircraft engine, and low-pressure turbine
US8632301B2 (en) 2012-01-31 2014-01-21 United Technologies Corporation Low noise compressor rotor for geared turbofan engine
US8517668B1 (en) 2012-01-31 2013-08-27 United Technologies Corporation Low noise turbine for geared turbofan engine
WO2013147974A3 (en) * 2012-01-31 2013-11-28 United Technologies Corporation Low noise turbine for geared turbofan engine
US8246292B1 (en) * 2012-01-31 2012-08-21 United Technologies Corporation Low noise turbine for geared turbofan engine
US8714913B2 (en) 2012-01-31 2014-05-06 United Technologies Corporation Low noise compressor rotor for geared turbofan engine
US12123432B2 (en) 2012-01-31 2024-10-22 Rtx Corporation Low noise turbine for geared turbofan engine
US9733266B2 (en) 2012-09-28 2017-08-15 United Technologies Corporation Low noise compressor and turbine for geared turbofan engine
US9650965B2 (en) 2012-09-28 2017-05-16 United Technologies Corporation Low noise compressor and turbine for geared turbofan engine
US9726019B2 (en) 2012-09-28 2017-08-08 United Technologies Corporation Low noise compressor rotor for geared turbofan engine
US9624834B2 (en) 2012-09-28 2017-04-18 United Technologies Corporation Low noise compressor rotor for geared turbofan engine
US8834099B1 (en) 2012-09-28 2014-09-16 United Technoloiies Corporation Low noise compressor rotor for geared turbofan engine
US11143109B2 (en) 2013-03-14 2021-10-12 Raytheon Technologies Corporation Low noise turbine for geared gas turbine engine
US11168614B2 (en) 2013-03-14 2021-11-09 Raytheon Technologies Corporation Low noise turbine for geared gas turbine engine
US11560849B2 (en) 2013-03-14 2023-01-24 Raytheon Technologies Corporation Low noise turbine for geared gas turbine engine
US11719161B2 (en) 2013-03-14 2023-08-08 Raytheon Technologies Corporation Low noise turbine for geared gas turbine engine
CN112228402A (en) * 2020-09-25 2021-01-15 杭州微光电子股份有限公司 Fan guiding device
CN112228402B (en) * 2020-09-25 2022-03-29 杭州微光电子股份有限公司 Fan guiding device

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CH478994A (en) 1969-09-30
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AT242856B (en) 1965-10-11

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