GB1019158A - Improvements in or relating to axial-flow compressor,blower or fan with reduced noisiness - Google Patents
Improvements in or relating to axial-flow compressor,blower or fan with reduced noisinessInfo
- Publication number
- GB1019158A GB1019158A GB20781/64A GB2078164A GB1019158A GB 1019158 A GB1019158 A GB 1019158A GB 20781/64 A GB20781/64 A GB 20781/64A GB 2078164 A GB2078164 A GB 2078164A GB 1019158 A GB1019158 A GB 1019158A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blades
- diameter
- axial
- stator
- rotor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
1,019,158. Axial-flow compressors, blowers and fans. J. JENIE, J. NEMEC and Z. MORAVEC, May 20, 1964 [May 21, 1963], No. 20781/64. Heading F1C. Noise in an axial-flow compressor, blower or fan is reduced by arranging that #/#o is greater than 0À65, where To is the circumferential pitch of the blades of either the stator 1, Fig. 2, or the rotor 2, measured at the tip diameter D 2 , Fig. 3, and # is determined graphically as follows. A point B on the trailing edge 3 of a stator blade at a diameter D is projected at b on to the conical surface of revolution described by the leading edge 4 of a rotor blade, intersecting this surface at a point B<SP>1</SP>. The locus of all such points B<SP>1</SP>, from the root diameter D 1 to the tip diameter D 2 , when further projected parallel to the axis O of rotation on to a plane at right angles to this axis forms a trace 3<SP>1</SP> on that plane of the trailing edge 3. The leading edge 4 is similarly projected on to this plane to form a trace 4<SP>1</SP>. If these traces 3<SP>1</SP> and 4<SP>1</SP> are rotated about the axis O until they have a common point E on the root diameter D 1 , they subtend at the tip diameter D 2 the required value #. A similar construction can be applied in the case in which the stator blades follow the rotor blades instead of preceding them. The optimum value of S is Z r /Z s , where Z r is the number of rotor blades and Z s is the number of stator blades. Preferably, Z r /Z s = 1/k, i/2, where i is an integral positive odd number and k is an integral positive number or Z r /Z s = 1/k (i-2/3) or 1/k (i-1/3), where i and k are integral positive numbers.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CS290063 | 1963-05-21 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1019158A true GB1019158A (en) | 1966-02-02 |
Family
ID=5367464
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB20781/64A Expired GB1019158A (en) | 1963-05-21 | 1964-05-20 | Improvements in or relating to axial-flow compressor,blower or fan with reduced noisiness |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US3270953A (en) |
| AT (1) | AT242856B (en) |
| CH (1) | CH478994A (en) |
| DE (1) | DE1428141B2 (en) |
| GB (1) | GB1019158A (en) |
Families Citing this family (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3574477A (en) * | 1969-02-19 | 1971-04-13 | Boeing Co | Noise attenuating system for rotary engines |
| CH516747A (en) * | 1970-05-27 | 1971-12-15 | Bbc Brown Boveri & Cie | Method and blading to reduce the snaking movement of a mass particle when flowing through a turbo machine |
| 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 |
| GB2054058B (en) * | 1979-06-16 | 1983-04-20 | Rolls Royce | Reducing rotor noise |
| 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 |
| FR2719551B1 (en) * | 1994-05-04 | 1996-07-12 | Eurocopter France | Anti-torque device with faired rotor and stator rectifier and inclined rectifier vanes. |
| FR2719550B1 (en) * | 1994-05-04 | 1996-07-26 | Eurocopter France | Anti-torque device with faired rotor and stator rectifier, and phase modulation of the rotor blades, for helicopters. |
| DE102004016246A1 (en) * | 2004-04-02 | 2005-10-20 | Mtu Aero Engines Gmbh | Turbine, in particular low-pressure turbine, a gas turbine, in particular an aircraft engine |
| 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 |
| US20160138474A1 (en) | 2012-09-28 | 2016-05-19 | 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 |
| US11719161B2 (en) | 2013-03-14 | 2023-08-08 | Raytheon Technologies Corporation | Low noise turbine for geared gas turbine engine |
| US10605172B2 (en) | 2013-03-14 | 2020-03-31 | United Technologies Corporation | Low noise turbine for geared gas turbine engine |
| CN112228402B (en) * | 2020-09-25 | 2022-03-29 | 杭州微光电子股份有限公司 | Fan guiding device |
Family Cites Families (4)
| 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 |
-
1964
- 1964-05-19 US US368649A patent/US3270953A/en not_active Expired - Lifetime
- 1964-05-19 CH CH649964A patent/CH478994A/en not_active IP Right Cessation
- 1964-05-20 GB GB20781/64A patent/GB1019158A/en not_active Expired
- 1964-05-20 DE DE19641428141 patent/DE1428141B2/en active Pending
- 1964-05-21 AT AT441964A patent/AT242856B/en active
Also Published As
| Publication number | Publication date |
|---|---|
| US3270953A (en) | 1966-09-06 |
| DE1428141A1 (en) | 1969-01-23 |
| AT242856B (en) | 1965-10-11 |
| CH478994A (en) | 1969-09-30 |
| DE1428141B2 (en) | 1972-10-19 |
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