US2920813A - Gas reaction rotors - Google Patents
Gas reaction rotors Download PDFInfo
- Publication number
- US2920813A US2920813A US706653A US70665358A US2920813A US 2920813 A US2920813 A US 2920813A US 706653 A US706653 A US 706653A US 70665358 A US70665358 A US 70665358A US 2920813 A US2920813 A US 2920813A
- Authority
- US
- United States
- Prior art keywords
- blades
- rotor
- slots
- faces
- gas
- 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 - Lifetime
Links
Images
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
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/148—Blades with variable camber, e.g. by ejection of fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
- F04D25/045—Units comprising pumps and their driving means the pump being fluid-driven the pump wheel carrying the fluid driving means, e.g. turbine blades
-
- 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 gas reaction rotors, and relates more particularly to the rotors of centrifugal fans.
- My invention is an improvement over the one disclosed in said application in that I provide the fan blades between the trailing ends of their driving and trailing faces with peripheral faces in which the air discharge slots are placed, the inner surfaces of the driving and trailing faces being curved to cause the air jets to be discharged forwardly in the direction of rotation past the trailing ends of the driving faces.
- This provides a more rugged blade construction with wider jet slots and wider air passages leading to the slots.
- An object of this invention is to improve airfoil blades used in gas reaction rotors and from which gas under pressure is projected for improving the performances of the rotors.
- Another object of this invention is to provide an airfoil blade for a gas reaction rotor with a blunt instead of a sharp trailing edge, and to project gas under pressure from within the blade, forwardly through a slot in the blunt trailing edge for improving the performance of the rotor.
- Fig. 1 is an end elevation of a double-inlet, centrifugal fan rotor embodying this invention, a portion of the adjacent front plate being removed, and several blades and the fan shaft shown in section;
- Fig. 2 is a side elevation of the rotor of Fig. 1, and shows also a source of compressed air connected through passages in the rotor to the interiors of the blades, and
- Fig. 3 is an enlarged sectional view of one of the fan blades.
- the fan rotor has a center plate and front or side plates 11 with airfoil blades 12 supported between the center plate 10 and each side plate 11.
- the side plates 11 have the usual axial inlet openings 13.
- the center plate 10 is attached by supports 14 to a rotary shaft 15.
- the shaft 15 has a central air passage 16 which extends through a seal 17, and is connected through a valve 18 and tubing 19 to a compressed air source 20.
- the valve 18 has an adjusting handle 21 with an indicator 22 on one end, the indicator 22 being opposite a scale 23 calibrated in terms of volume or pressure.
- the center plate 10 has an opening 25 around the passage 16 into which the passage 16 discharges through a slot 26. Radial passages 28 in the center plate 10 connect with the opening 25 and with transverse passages 29 which line up with the hollow interiors of'the blades 12.
- the blades 12 instead of having the usual sharp trailing edges, have between the trailing ends of their driving faces 30 and their longer trailing faces 31, forwardly (counter-clockwise in the direction of rotation) inclined peripheral faces 32 through which extend forwardly curved jet slots 33.
- the inner surface of each driving face 30 has an inwardly extending, curved bulge 34 forming one side of a slot 33 and providing a constriction for increasing the velocity of the air supplied through a slot 33.
- the jets of air projected from the slots 33 can increase the pressure added to the gas upon which the rotor works by as much as 40% more than is provided with the air jets shut off.
- the percentage of pressure increase can be varied by adjustment of the valve 18.
- backwardly curved airfoil blades are defined as airfoil blades having convex gas impacting or driving faces, having leading edges or. noses which first impact the gas handled by the blades, and having trailing ends which are downstream with respect to gas flow of their noses.
- the center plate of a double inlet fan is, of course, the back plate of each fan section, and corresponds to the back plate of a fan having but a single rotor section. Therefore, the term back plate as used in the annexed claim should be considered as a center plate where the fan involved is a double inlet fan.
- a centrifugal fan rotor having a side plate and a back plate, a plurality of backwardly curved airfoil blades supported between said plates, said side plate having an axial inlet opening, the noses of said blades being located adjacent the edge of said opening, the trailing faces of said blades being longer than their driving faces, said blades having forwardly inclined peripheral faces between the trailing ends of their driving and trailing faces, said peripheral faces being located adjacent the periphery of said rotor, said peripheral faces having slots therein, said blades having means within their interiors forming 3 passages connected-"to saidv slots, and means-for supplying compressed gas into said passages and out said slots, said passages being forwardly curved where they connect with said slots.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
-Jan.,12, 1960 'F[ R. GOLDSCHMIED 2,920,813
GAS REACTION ROTORS Filed Jan. 2, 195a COMPRESSED AIR SOURCE FABIO R. GOLDSCHMIED INVENTOR ATTORNEY United States PatentC c 1 GAS REACTION ROTORS Fablo R. Goldscbmied, West Roxbury, Mass., assignor to Westinghouse Electric Corporation, East Pittsburgh, Pa., a corporation of Pennsylvania Application January 2, 1958, Serial No. 706,653
1 Claim. (Cl. 230-134) This invention relates to gas reaction rotors, and relates more particularly to the rotors of centrifugal fans.
In the co-pending application of John E. McDonald, Serial No. 627,459, filed December 10, 1956, there is disclosed a method of increasing the gas pressure from a centrifugal fan by blowing gas such as air, from the interiors of airfoil blades forwardly through slots in the driving faces of the blades adjacent to the trailing edges of the blades, at substantial angles to the chord lines of the blades. This method has several important advantages. It enables a small, less expensive rotor to provide the same increase in gas pressure that a larger, more expensive rotor has previously provided. It enables a rotor designed for normal loads to easily handle peak loads. It also provides an effective volume control since the flow of air out of the slots can be varied for varying the pressure increase provided by a fan.
My invention is an improvement over the one disclosed in said application in that I provide the fan blades between the trailing ends of their driving and trailing faces with peripheral faces in which the air discharge slots are placed, the inner surfaces of the driving and trailing faces being curved to cause the air jets to be discharged forwardly in the direction of rotation past the trailing ends of the driving faces. This provides a more rugged blade construction with wider jet slots and wider air passages leading to the slots.
An object of this invention is to improve airfoil blades used in gas reaction rotors and from which gas under pressure is projected for improving the performances of the rotors.
Another object of this invention is to provide an airfoil blade for a gas reaction rotor with a blunt instead of a sharp trailing edge, and to project gas under pressure from within the blade, forwardly through a slot in the blunt trailing edge for improving the performance of the rotor.
This invention will now be described with reference to the annexed drawings, of which:
Fig. 1 is an end elevation of a double-inlet, centrifugal fan rotor embodying this invention, a portion of the adjacent front plate being removed, and several blades and the fan shaft shown in section;
Fig. 2 is a side elevation of the rotor of Fig. 1, and shows also a source of compressed air connected through passages in the rotor to the interiors of the blades, and
Fig. 3 is an enlarged sectional view of one of the fan blades.
The fan rotor has a center plate and front or side plates 11 with airfoil blades 12 supported between the center plate 10 and each side plate 11. The side plates 11 have the usual axial inlet openings 13. The center plate 10 is attached by supports 14 to a rotary shaft 15.
Patented Jan. 12, 1960 The shaft 15 has a central air passage 16 which extends through a seal 17, and is connected through a valve 18 and tubing 19 to a compressed air source 20. The valve 18 has an adjusting handle 21 with an indicator 22 on one end, the indicator 22 being opposite a scale 23 calibrated in terms of volume or pressure.
The center plate 10 has an opening 25 around the passage 16 into which the passage 16 discharges through a slot 26. Radial passages 28 in the center plate 10 connect with the opening 25 and with transverse passages 29 which line up with the hollow interiors of'the blades 12.
The blades 12 instead of having the usual sharp trailing edges, have between the trailing ends of their driving faces 30 and their longer trailing faces 31, forwardly (counter-clockwise in the direction of rotation) inclined peripheral faces 32 through which extend forwardly curved jet slots 33. The inner surface of each driving face 30 has an inwardly extending, curved bulge 34 forming one side of a slot 33 and providing a constriction for increasing the velocity of the air supplied through a slot 33.
When the valve 18 is opened, compressed air is supplied from the source 20 through the passage 16, slot 26, opening 25 and passages 28 and 29 into the hollow interiors 35 of the blades, and from the blades through the slots 33. The slots 33 are arranged to discharge jets of air outwardly and forwardly past the driving faces 30 of the blades.
With the rotor rotating in a counter-clockwise direction as shown by the arrow of Fig. 1, the jets of air projected from the slots 33 can increase the pressure added to the gas upon which the rotor works by as much as 40% more than is provided with the air jets shut off. The percentage of pressure increase can be varied by adjustment of the valve 18. i
The air jets projected from the blades do not maintain boundary layer flow. On the contrary, they greatly disturb boundary layer flow, and act somewhat as flaps,
but without the mass of flaps and their mechanical problems of adjustment, and not being acted upon by the tremendous centrifugal force to which hinged physical fiaps would be subjected if used on centrifugal fan blades.
In the annexed claim backwardly curved airfoil blades are defined as airfoil blades having convex gas impacting or driving faces, having leading edges or. noses which first impact the gas handled by the blades, and having trailing ends which are downstream with respect to gas flow of their noses.
The center plate of a double inlet fan, is, of course, the back plate of each fan section, and corresponds to the back plate of a fan having but a single rotor section. Therefore, the term back plate as used in the annexed claim should be considered as a center plate where the fan involved is a double inlet fan.
What I claim is:
A centrifugal fan rotor having a side plate and a back plate, a plurality of backwardly curved airfoil blades supported between said plates, said side plate having an axial inlet opening, the noses of said blades being located adjacent the edge of said opening, the trailing faces of said blades being longer than their driving faces, said blades having forwardly inclined peripheral faces between the trailing ends of their driving and trailing faces, said peripheral faces being located adjacent the periphery of said rotor, said peripheral faces having slots therein, said blades having means within their interiors forming 3 passages connected-"to saidv slots, and means-for supplying compressed gas into said passages and out said slots, said passages being forwardly curved where they connect with said slots.
References Cited in the file of this patent UNITED STATES PATENTS 390,508 Mosher et Oct. 2, 1888 S'talker' Dec. 15, 1942 Stalker July 12, 1949 FOREIGN PATENTS Great Britain Mar. 14, 1949 Great Britain May 18, 1955 Great Britain Oct. 10, 1956 France a Nov. 28, 1938
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US706653A US2920813A (en) | 1958-01-02 | 1958-01-02 | Gas reaction rotors |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US706653A US2920813A (en) | 1958-01-02 | 1958-01-02 | Gas reaction rotors |
Publications (1)
Publication Number | Publication Date |
---|---|
US2920813A true US2920813A (en) | 1960-01-12 |
Family
ID=24838513
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US706653A Expired - Lifetime US2920813A (en) | 1958-01-02 | 1958-01-02 | Gas reaction rotors |
Country Status (1)
Country | Link |
---|---|
US (1) | US2920813A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3485484A (en) * | 1966-10-20 | 1969-12-23 | Venot Pic Sa | Device for the circulation and the aeration of fluids |
US4228753A (en) * | 1979-02-27 | 1980-10-21 | The United States Of America As Represented By The Secretary Of The Navy | Fluidic controlled diffusers for turbopumps |
US5480291A (en) * | 1990-02-05 | 1996-01-02 | Underwater Excavation Limited | Underwater excavation apparatus |
WO2008057627A2 (en) * | 2006-05-18 | 2008-05-15 | Honeywell International Inc. | Flow-control technique to vector bulk flow leaving a vane |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US390508A (en) * | 1888-10-02 | Draft | ||
FR838209A (en) * | 1937-05-21 | 1939-03-01 | Vickers Aviat Ltd | Propeller refinements |
US2305226A (en) * | 1940-01-05 | 1942-12-15 | Edward A Stalker | Blower |
GB619722A (en) * | 1946-12-20 | 1949-03-14 | English Electric Co Ltd | Improvements in and relating to boundary layer control in fluid conduits |
US2476002A (en) * | 1946-01-12 | 1949-07-12 | Edward A Stalker | Rotating wing |
GB730147A (en) * | 1952-08-28 | 1955-05-18 | Oerlikon Maschf | Blading for radial flow centrifugal compressors, blowers, fans, pumps and the like |
GB758906A (en) * | 1953-12-31 | 1956-10-10 | Westinghouse Electric Int Co | Improvements in or relating to centrifugal fans |
-
1958
- 1958-01-02 US US706653A patent/US2920813A/en not_active Expired - Lifetime
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US390508A (en) * | 1888-10-02 | Draft | ||
FR838209A (en) * | 1937-05-21 | 1939-03-01 | Vickers Aviat Ltd | Propeller refinements |
US2305226A (en) * | 1940-01-05 | 1942-12-15 | Edward A Stalker | Blower |
US2476002A (en) * | 1946-01-12 | 1949-07-12 | Edward A Stalker | Rotating wing |
GB619722A (en) * | 1946-12-20 | 1949-03-14 | English Electric Co Ltd | Improvements in and relating to boundary layer control in fluid conduits |
GB730147A (en) * | 1952-08-28 | 1955-05-18 | Oerlikon Maschf | Blading for radial flow centrifugal compressors, blowers, fans, pumps and the like |
GB758906A (en) * | 1953-12-31 | 1956-10-10 | Westinghouse Electric Int Co | Improvements in or relating to centrifugal fans |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3485484A (en) * | 1966-10-20 | 1969-12-23 | Venot Pic Sa | Device for the circulation and the aeration of fluids |
US4228753A (en) * | 1979-02-27 | 1980-10-21 | The United States Of America As Represented By The Secretary Of The Navy | Fluidic controlled diffusers for turbopumps |
US5480291A (en) * | 1990-02-05 | 1996-01-02 | Underwater Excavation Limited | Underwater excavation apparatus |
US5607289A (en) * | 1990-02-05 | 1997-03-04 | Underwater Excavation Ltd. | Underwater excavation apparatus |
WO2008057627A2 (en) * | 2006-05-18 | 2008-05-15 | Honeywell International Inc. | Flow-control technique to vector bulk flow leaving a vane |
WO2008057627A3 (en) * | 2006-05-18 | 2008-07-10 | Honeywell Int Inc | Flow-control technique to vector bulk flow leaving a vane |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US2991929A (en) | Supersonic compressors | |
US2435236A (en) | Superacoustic compressor | |
US2735612A (en) | hausmann | |
US2401826A (en) | Turbine | |
JP4482732B2 (en) | Method and apparatus for assembling a gas turbine engine | |
US5437541A (en) | Blade for axial fan | |
US2934259A (en) | Compressor blading | |
US2920864A (en) | Secondary flow reducer | |
US2918254A (en) | Turborunner | |
US3804335A (en) | Vaneless supersonic nozzle | |
US2974927A (en) | Supersonic fluid machine | |
US2933238A (en) | Axial flow compressors incorporating boundary layer control | |
JPH01121599A (en) | Radial discharge centrifugal compressor | |
US20160312618A1 (en) | Rotor assembly with scoop | |
US6312221B1 (en) | End wall flow path of a compressor | |
GB754055A (en) | Improvements in or relating to centrifugal fan wheels | |
US2920813A (en) | Gas reaction rotors | |
US2953295A (en) | Supersonic compressor with axially transverse discharge | |
US20060018753A1 (en) | High pressure tandem turbine | |
US2870957A (en) | Compressors | |
US3006534A (en) | Centrifugal fans | |
US2362514A (en) | Centrifugal compressor | |
US2806645A (en) | Radial diffusion compressors | |
US2935245A (en) | Gas reaction rotors | |
US2874894A (en) | Gas reaction rotors |