US2344835A - Pump - Google Patents
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- US2344835A US2344835A US497762A US49776243A US2344835A US 2344835 A US2344835 A US 2344835A US 497762 A US497762 A US 497762A US 49776243 A US49776243 A US 49776243A US 2344835 A US2344835 A US 2344835A
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- Prior art keywords
- blades
- slot
- casing
- blade
- hollow
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Classifications
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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
- F04D19/00—Axial-flow pumps
- F04D19/02—Multi-stage pumps
- F04D19/028—Layout of fluid flow through the stages
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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
- F04D19/00—Axial-flow pumps
- F04D19/02—Multi-stage pumps
- F04D19/024—Multi-stage pumps with contrarotating parts
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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
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/009—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids by bleeding, by passing or recycling fluid
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- 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
- FIG. 2 A. STALKER PUMP Filed Aug- 7, 1943 HIFI M FIG. 2
- FIG. 1 A first figure.
- My invention relates to pumps having impeller blades or guide vanes. It has for its principal object to provide a simple .and self-contained pump arrangement in which the lift of the blades is increased while the drag or resistance encountered thereby is decreased, and in which the blades are made to function eiiiciently and effectively over a wide range of back pressures. ⁇ It is also 'anobject to develop a system of boundary layer control for the surface ofthe blades making direct use of the pressure differentials which exist within the pump usen. It is a sun further object to provide sets of blades withinthe pump having surface slots therein ⁇ and ⁇ interconnected with ⁇ each other so that ⁇ a downstream blade in a zone form of construction of the impeller;
- Fig. 3 shows schematically how the blades of such construction are interconnected by a duct
- Figs. 4 and 5 are sectional views through the. blades on the lines 4--4 and 5-5 respectively of F1s.3; y i n Fig. 6 is a view similar to Fig. 2 showing a a modified form of construction;
- Fig. 7 is a schematic view of the duct connections of such modified construction and Figs. 8 and 9 are section views through the blades on the lines 8-8 Iand 0-8 of Fig. 'I re-
- the pump case is l
- the inletis 2 and the exit is 3.
- the impeller hub is l having fixed ⁇ to it the bladesl forming a series of impellers ⁇ disposed along theaxis of the pump.
- the guide ⁇ vanes are 6 also disposed along theaxis and alternated with the impeller blades.
- the hub is fixed to the shaft 1 which rotates the impeller blade 5 relative to the guide vanes i.
- the blades are arranged in axially spaced relation with each pair of adjacent blades in an axial plane, such as 5a and 5b, constituting a set and the blades of each set being interconnected by means of separate air ow conduits 8.
- the blade sets are staggered in a peripheral direction, preferably as shown in Fig.
- each alternateset is offset, and provi- Vsion is thus made for separately interconnecting each pair of blades by the several conduits 8.
- the blades 5 and 5a of the rotating element alternate with similarly arranged guide vanes or blades and 6 and 6a of the casing.
- the blades of the casing are also arranged with pairs of adjacent blades in the same axial plane forming a set and being interconnected by separate conduits lor ducts il.
- the sets of stator blades are staggered similarly to those on the rotor and arranged to alternate with thoseonthe rotor as shown in Fig. l.
- the biades have hollow interiors and are formed kwith surface slots t and I0 on the suction or convex surfaces thereof. As will be seen from Fig. 5, slot III has overlapping walls to direct the slot jet rearward substantially along the surface of the blade.
- blade 5a is located in a zone of higher pressure and hence its slot 9 acts to inducta iiow ⁇ of air in the direction of the arrows shown in Figs. 3 and 4. Such flow passes through conduit 8 and into the hollow interior of blade 5b which is upstream and hence in a zone' of lower pressure. The ilow is then discharged from slot I0 over the surface of the blade inthe direction indicated by the arrows in Figs. 3 and 5.
- the flow as inducted over the surface of one blade and as discharged over the surface of the other acts to impart additional energy to the boundary layer on the surface of both blades, reducing the tendency of the boundary layer to drag and to separate from the blade surface and causing the external or main now to follow the blade surface to large angles of attack.
- Such additional energizing of the boundary layer produces an increase in lift and a reduction in drag, and makesit possible for the blade to operate efliciently overa wide range of lift angles and against substantial variation in back pressures.
- the blades 6 and 6a on the casing function in a similar manner to that described for the rotating blades, thus providing eicient over-all operation.
- a casing aplurality of hollow blades of which some are supported for rotation in the casing. said blades upon rotation developing a iiuid flow relative thereto, said flow possessing regions of different pressures at different blades, and means defining a closed duct communicating between the interiors of at least two blades situated in regions of different fluid pressure, one of said blades having an induction.
- slot and the other a discharge vslot in its exterior wall inkcommunication with its hollow interior so that a common .slot flow is induced by the pressure difference to control the ilow about the two blades.
- a casing adapted to receive a fluid flow, a plurality of hollow blades vsupported inthe casing for rotation about an axis, said blades upon'rotation developing a fluid ow through said casing relative ⁇ to said blades and possessing regions of different pressures at different blades, and means defining a duct communicating between the interiorsof at least two blades situated in regions vof different fluid pressure, one of said blades "having an induction slot and the other a discharge slot in its wall in communication with its hollow interior and with said duct to utilize'the same now for control of the boundary layer on both blades.
- a plurality of hollow blades supported in the casing to form a pluralityof stages spaced axially, andmeans defining a duct communicating through the ends of two blades with their interiors, said bladesbeingrdisplaced axially on opposite sides lof an intervening stage, said blades having slots in their external walls in communication with their hol- ⁇ pressure having a low interiors and ⁇ said duct, the'blades of said intervening stage being staggered relative to the blades having said duct to provide access for the duct through saidV intervening stage.
- a casing adapted to receive a fluid iiow, a plurality of hollow blades arranged in sets and supported in said casing for rotation about an axis, said blades upon rotation developing a fluid viiow through said casing relative to said blades and possessing regions of diierent pressures at diierent blades, one of the blades of a set having an induction slot for inducting a flow and another blade of the same set situated in a region of different discharge slotin its wall in communication with its hollow interior, and
- 'means defining a duct communicating between the interiors of said two blades to conduct the same flow from onefof said blades to the other to I provide control of the boundary layers on both of said blades.
- a casing In combination in a fluid machine, a casing, a. rotating element within vsaid casing, a plurality of blades supported in said casing, a prurality of hollow blades carried on said rotating element and-arranged in sets, a duct communicating between the interiors of the blades of each set, said hollow blades having slots on the surfaces thereof in communication with said hollow interiors providing for the induction of a flow throughfthe slot of the downstream blade of a set and discharge of the same flow from the slot of the upstream yblade of said set to control the boundary layers'onboth said blades.
- a casing In Combination in a fluid machine, a casing, a rotating element within said casing, a plurality of blades supported in said casing, a plurality of hollow blades carried on said rotating element andarrang'ed* in sets, a duct communicating between the interiors of the blades of each set, said hollow blades having slots on the convex surfaces thereof in communication with said hollow'interiors providing Vfor Ithe induction of a flow through the slot of the downstream blade o a set and discharge of the same flow from the slot of the upstream blade of said set to control the boundary layers on both said blades.
- a casing In combination in a fluid machine, a casing, a rotating element within said casing, a plurality of hollow' blades supported by said casing and arranged in sets, a plurality of hollow blades carried on said rotating element and also arranged in sets, and a duct communicating between the interiors of the blades of each set, ⁇ said blades having slots on the surfaces thereof in communication with said hollow interiors providing for induction of a flow through the slot of the downstream blade of a set and discharge of the ysame flow from the slot of the upstream blade of said set.
- a casing a rotating element within said casing, a plublades carried on said rotating element and also arranged in pairs, said stator blades alternating with those of said rotating element, and a duct communicating between the interiors oi the blades of each pair, said blades having slots on the surfaces thereof in communication with said hollow interiors providing lor the induction oi? a iiow through the slot oi the downstreamA blade oi a pair and discharge o1" the saine how i'r 'n the slot oi the upstream blade oi said pair.
- a casing, o, hub within the casing and defining therewith an annular passage therebetween, said hub being rotatable about an. axis, a plurality of hollow blades carried on said hub in said passage and adapted to develop a relative ⁇ flow therethrough, said blades forming a, plurality of ariially related stages, a blade of one stage located downstream in a zone of relatively higher pressure having an induction slot in its lower surface in communication with its interior, a blade of a second stage located upstream in a zone of relatively lower pressure having a discharge slot in its lower surface, the interiors of said blades being in communication to conduct a iiow from said induction slot to said discharge slot.
- a casing In combination in a fluid machine, a casing, a hub within the casing and dening therewith an annular passage therebetween, said hub bein rotatable about an axis, a plurality of hollow lades carried on said hub in said casing and arranged with adjacent blades in the same axial plane forming a set, a blade of one set located downstream in a zone of relatively higher pressure having an induction slot in its lower nose surface in communication with its interior,
- another blade of said set being located upstream in a zone oi relatively lower pressure and havaxial plane forming a set, the blade sets being staggered in a peripheral direction, a blade oi one set located downstream in a sono oi rela@ tively higher1 pressure having an induction. slot in its lower nose surface in communication with its interior, another blade of said set being lo cated upstream in a zone of relatively" lower pressure and having a discharge slot in its lower nose surface, and a duct communicating between the interiors ci the blades ci each set to conduct a flow from said induction slot to said discharge slot to control the boundary layers on both blades of said set by a cornnion flow.
- a casing In combination in a huid machine, a casing, a hub within the casing and dening there with an annular passage therebetween, said hub being rotatable about an axis, a plurality of hollow blades carried on said hub and on said casing and arranged in an alternate relation in said passage for developing a relative flow therethrough, the blades of said hub and those of said casing forming a plurality of axially related stages, adjacent blades on said hub and on said casing respectively being arranged in sets, a blade of one set located downstream in a zone of relatively higher pressure having an induction slot in its lower nose surface in communication with its interior, another blade of said set located upstream in a zone of relatively lower pressure having a discharge slot in its lower nose surface, and duct means communicating between the interiors of the blades of the several sets for conducting a flow from said induction slot to said discharge slot to control the boundary layers on both blades or" said set by a common ow.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
March 21, 1944. E. A. STALKER PUMP Filed Aug- 7, 1943 HIFI M FIG. 2
FIG.
i I INVENTOR,
MM2-(M ATTORNEY5 spectively.
Patented Mar. 21, 1944 UNITED Nsm'rlezs PATENT oFFlcE Edward A. Stalker, Bayity, Mich. Application August 7, 1843, Scl'll N0. 497,732
('Cl. 23o-122) 14 Claims.
This case is a continuation-impart of my copending applications, Serial Number 447,822,
iiled June 20, 1942, entitled Pumps," and Serial Number 447,823, filed June20, 1942, entitled Blowers l My invention relates to pumps having impeller blades or guide vanes. It has for its principal object to provide a simple .and self-contained pump arrangement in which the lift of the blades is increased while the drag or resistance encountered thereby is decreased, and in which the blades are made to function eiiiciently and effectively over a wide range of back pressures.` It is also 'anobject to develop a system of boundary layer control for the surface ofthe blades making direct use of the pressure differentials which exist within the pump usen. It is a sun further object to provide sets of blades withinthe pump having surface slots therein `and `interconnected with `each other so that` a downstream blade in a zone form of construction of the impeller;
Fig. 3 shows schematically how the blades of such construction are interconnected by a duct;
Figs. 4 and 5 are sectional views through the. blades on the lines 4--4 and 5-5 respectively of F1s.3; y i n Fig. 6 is a view similar to Fig. 2 showing a a modified form of construction;
Fig. 7 is a schematic view of the duct connections of such modified construction and Figs. 8 and 9 are section views through the blades on the lines 8-8 Iand 0-8 of Fig. 'I re- In Fig. 1 the pump case is l, the inletis 2 and the exit is 3. The impeller hub is l having fixed `to it the bladesl forming a series of impellers `disposed along theaxis of the pump. The guide `vanes are 6 also disposed along theaxis and alternated with the impeller blades. The hub is fixed to the shaft 1 which rotates the impeller blade 5 relative to the guide vanes i.
As shown in Figs. 2 and 3, the bladesare arranged in axially spaced relation with each pair of adjacent blades in an axial plane, such as 5a and 5b, constituting a set and the blades of each set being interconnected by means of separate air ow conduits 8. The blade sets are staggered in a peripheral direction, preferably as shown in Fig.
2, so that each alternateset is offset, and provi- Vsion is thus made for separately interconnecting each pair of blades by the several conduits 8. The blades 5 and 5a of the rotating element alternate with similarly arranged guide vanes or blades and 6 and 6a of the casing. The blades of the casing are also arranged with pairs of adjacent blades in the same axial plane forming a set and being interconnected by separate conduits lor ducts il. The sets of stator blades are staggered similarly to those on the rotor and arranged to alternate with thoseonthe rotor as shown in Fig. l.
The biades have hollow interiors and are formed kwith surface slots t and I0 on the suction or convex surfaces thereof. As will be seen from Fig. 5, slot III has overlapping walls to direct the slot jet rearward substantially along the surface of the blade. Y
'I'he downstream. blade 5a is located in a zone of higher pressure and hence its slot 9 acts to inducta iiow` of air in the direction of the arrows shown in Figs. 3 and 4. Such flow passes through conduit 8 and into the hollow interior of blade 5b which is upstream and hence in a zone' of lower pressure. The ilow is then discharged from slot I0 over the surface of the blade inthe direction indicated by the arrows in Figs. 3 and 5.
The flow as inducted over the surface of one blade and as discharged over the surface of the other acts to impart additional energy to the boundary layer on the surface of both blades, reducing the tendency of the boundary layer to drag and to separate from the blade surface and causing the external or main now to follow the blade surface to large angles of attack. Such additional energizing of the boundary layer produces an increase in lift and a reduction in drag, and makesit possible for the blade to operate efliciently overa wide range of lift angles and against substantial variation in back pressures. By using `both an induction slot and a discharge slot located in 'zones of different pressure as generated by the blower itself. the same duct flow is made to serve a plurality of blades, and a highly efficient andV economical operation is secured.
vThis is an improvement over the design in my application Serial No. 399,310, Patent No. 2,314,- 058.
The blades 6 and 6a on the casing function in a similar manner to that described for the rotating blades, thus providing eicient over-all operation.
In the modified arrangement shown in Figs. 6 through 9, the construction and arrangement are essentially similar to that described above with respect to Figs. 1 through 5 with the exception that the suction slot 9' and the discharge slot I are formed on the lower nose surfaces ofthe blades a and 5b respectively, i. e., on the pressure or concave sides thereof. As will be seen lfrom Fig. 8, slot ID has overlapping walls to direct the slot jet rearwardly substantially along the surface of the blade.
'I'he parts are numbered similarly to the corresponding parts in the earlier described modication, and the construction and mode of operation are substantially the same so that the same will be readily understood without further detailed description.
While I have illustrated a certain specific form ofvthis invention it is to be understood that I do not intend to limit myself tothis exact form but intendto claim my invention broadly as indicated by the appended claims.
While the forms of apparatus herein described constitute a preferred embodiment of the invention, it is to be understood that the invention is I I not-limited to these precise forms of apparatus,
and that changes may be made therein without departing' from the scope of the invention which is defined in the appended claims.
What is claimed is; i
1. In combination in a fluid machine, :a casing, aplurality of hollow blades of which some are supported for rotation in the casing. said blades upon rotation developing a iiuid flow relative thereto, said flow possessing regions of different pressures at different blades, and means defining a closed duct communicating between the interiors of at least two blades situated in regions of different fluid pressure, one of said blades having an induction. slot and the other a discharge vslot in its exterior wall inkcommunication with its hollow interior so that a common .slot flow is induced by the pressure difference to control the ilow about the two blades.
2. In combination in a iiuid machine, a casing adapted to receive a fluid flow, a plurality of hollow blades vsupported inthe casing for rotation about an axis, said blades upon'rotation developing a fluid ow through said casing relative` to said blades and possessing regions of different pressures at different blades, and means defining a duct communicating between the interiorsof at least two blades situated in regions vof different fluid pressure, one of said blades "having an induction slot and the other a discharge slot in its wall in communication with its hollow interior and with said duct to utilize'the same now for control of the boundary layer on both blades.
3. In combination in a fluidmathine` a cas ing containing a fluid flow therein, a plurality of hollow blades supported in the casing to form a pluralityof stages spaced axially, andmeans defining a duct communicating through the ends of two blades with their interiors, said bladesbeingrdisplaced axially on opposite sides lof an intervening stage, said blades having slots in their external walls in communication with their hol- `pressure having a low interiors and` said duct, the'blades of said intervening stage being staggered relative to the blades having said duct to provide access for the duct through saidV intervening stage.
4. In combination, at least two wing-like hollow elements bathed by a relative flow and each having a slot in its surface, said elements being spaced from each other and located in a region of different fluid pressure, and a duct communicating between the said slots to conduct a flow arising from the pressure difference and inducted at the slot of one of said elements and discharged through the slot of the other of said elements to control the boundary layer on both said elements.
5. In combination in a fluid machine, a casing adapted to receive a fluid iiow, a plurality of hollow blades arranged in sets and supported in said casing for rotation about an axis, said blades upon rotation developing a fluid viiow through said casing relative to said blades and possessing regions of diierent pressures at diierent blades, one of the blades of a set having an induction slot for inducting a flow and another blade of the same set situated in a region of different discharge slotin its wall in communication with its hollow interior, and
'means defining a duct communicating between the interiors of said two blades to conduct the same flow from onefof said blades to the other to I provide control of the boundary layers on both of said blades.
6. In combination in a fluid machine, a casing, a. rotating element within vsaid casing, a plurality of blades supported in said casing, a prurality of hollow blades carried on said rotating element and-arranged in sets, a duct communicating between the interiors of the blades of each set, said hollow blades having slots on the surfaces thereof in communication with said hollow interiors providing for the induction of a flow throughfthe slot of the downstream blade of a set and discharge of the same flow from the slot of the upstream yblade of said set to control the boundary layers'onboth said blades.
7. In Combination in a fluid machine, a casing, a rotating element within said casing, a plurality of blades supported in said casing, a plurality of hollow blades carried on said rotating element andarrang'ed* in sets, a duct communicating between the interiors of the blades of each set, said hollow blades having slots on the convex surfaces thereof in communication with said hollow'interiors providing Vfor Ithe induction of a flow through the slot of the downstream blade o a set and discharge of the same flow from the slot of the upstream blade of said set to control the boundary layers on both said blades.
8. In combination in a fluid machine, a casing, a rotating element within said casing, a plurality of hollow' blades supported by said casing and arranged in sets, a plurality of hollow blades carried on said rotating element and also arranged in sets, and a duct communicating between the interiors of the blades of each set, `said blades having slots on the surfaces thereof in communication with said hollow interiors providing for induction of a flow through the slot of the downstream blade of a set and discharge of the ysame flow from the slot of the upstream blade of said set.
9. In combination in a uid machine, a casing, a rotating element within said casing, a plublades carried on said rotating element and also arranged in pairs, said stator blades alternating with those of said rotating element, and a duct communicating between the interiors oi the blades of each pair, said blades having slots on the surfaces thereof in communication with said hollow interiors providing lor the induction oi? a iiow through the slot oi the downstreamA blade oi a pair and discharge o1" the saine how i'r 'n the slot oi the upstream blade oi said pair.
3.0. lin combination in fluid machine, ing, a hub within. the casing and deiining there with an annular passage therebetween, hub being rotatably borne in said machine, a plun rality of `hollow blades carried on said hub in said passage and adapted to develop relative :dow therethrough, said blades forming a plu rality of axially related stages, a blade of `one stage having a slot in its lower surface in coinn rnunication with its hollow interior, a blade or another stage at a zone of different pressure having a slot in its lower surface in communication with its interior, and a duct eornmunicating between said interiors to conduct a flow from one of said slots to the other.
il. in combination in a huid machine, a casing, o, hub within the casing and defining therewith an annular passage therebetween, said hub being rotatable about an. axis, a plurality of hollow blades carried on said hub in said passage and adapted to develop a relative `flow therethrough, said blades forming a, plurality of ariially related stages, a blade of one stage located downstream in a zone of relatively higher pressure having an induction slot in its lower surface in communication with its interior, a blade of a second stage located upstream in a zone of relatively lower pressure having a discharge slot in its lower surface, the interiors of said blades being in communication to conduct a iiow from said induction slot to said discharge slot.
l2. In combination in a fluid machine, a casing, a hub within the casing and dening therewith an annular passage therebetween, said hub bein rotatable about an axis, a plurality of hollow lades carried on said hub in said casing and arranged with adjacent blades in the same axial plane forming a set, a blade of one set located downstream in a zone of relatively higher pressure having an induction slot in its lower nose surface in communication with its interior,
lll
another blade of said set being located upstream in a zone oi relatively lower pressure and havaxial plane forming a set, the blade sets being staggered in a peripheral direction, a blade oi one set located downstream in a sono oi rela@ tively higher1 pressure having an induction. slot in its lower nose surface in communication with its interior, another blade of said set being lo cated upstream in a zone of relatively" lower pressure and having a discharge slot in its lower nose surface, and a duct communicating between the interiors ci the blades ci each set to conduct a flow from said induction slot to said discharge slot to control the boundary layers on both blades of said set by a cornnion flow.
la. In combination in a huid machine, a casing, a hub within the casing and dening there with an annular passage therebetween, said hub being rotatable about an axis, a plurality of hollow blades carried on said hub and on said casing and arranged in an alternate relation in said passage for developing a relative flow therethrough, the blades of said hub and those of said casing forming a plurality of axially related stages, adjacent blades on said hub and on said casing respectively being arranged in sets, a blade of one set located downstream in a zone of relatively higher pressure having an induction slot in its lower nose surface in communication with its interior, another blade of said set located upstream in a zone of relatively lower pressure having a discharge slot in its lower nose surface, and duct means communicating between the interiors of the blades of the several sets for conducting a flow from said induction slot to said discharge slot to control the boundary layers on both blades or" said set by a common ow.
EDWARD A. STALKER.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US497762A US2344835A (en) | 1943-08-07 | 1943-08-07 | Pump |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US497762A US2344835A (en) | 1943-08-07 | 1943-08-07 | Pump |
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US2344835A true US2344835A (en) | 1944-03-21 |
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US497762A Expired - Lifetime US2344835A (en) | 1943-08-07 | 1943-08-07 | Pump |
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Cited By (38)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2418221A (en) * | 1944-10-30 | 1947-04-01 | Curtis Pump Co | Liquid and vapor separating pump |
US2418801A (en) * | 1942-03-25 | 1947-04-08 | Vickers Electrical Co Ltd | Internal-combustion turbine plant |
US2501614A (en) * | 1947-11-28 | 1950-03-21 | Lockheed Aircraft Corp | Compressor construction |
US2520697A (en) * | 1943-10-11 | 1950-08-29 | Vickers Electrical Co Ltd | Internal-combustion turbine plant |
US2527971A (en) * | 1946-05-15 | 1950-10-31 | Edward A Stalker | Axial-flow compressor |
US2597510A (en) * | 1947-04-15 | 1952-05-20 | Worthington Pump & Mach Corp | Blade element for rotary fluid machines |
US2613028A (en) * | 1946-01-08 | 1952-10-07 | Rolls Royce | Air compressor for use on aircraft |
US2637487A (en) * | 1948-03-09 | 1953-05-05 | James G Sawyer | Blower |
US2647366A (en) * | 1946-06-24 | 1953-08-04 | William J Mccann | Means for preventing ice formation in jet propulsion and gas turbine engines |
US2656096A (en) * | 1946-01-04 | 1953-10-20 | Rateau Soc | Centrifugal pump and compressor |
US2682363A (en) * | 1950-12-08 | 1954-06-29 | Rolls Royce | Gas turbine engine |
US2685405A (en) * | 1948-05-03 | 1954-08-03 | Edward A Stalker | Axial flow compressor |
US2698129A (en) * | 1949-05-12 | 1954-12-28 | Joy Mfg Co | Multistage axial fan with boundary layer control |
US2709337A (en) * | 1952-03-28 | 1955-05-31 | United Aircraft Corp | Boundary layer control for the diffuser of a gas turbine |
US2720356A (en) * | 1952-06-12 | 1955-10-11 | John R Erwin | Continuous boundary layer control in compressors |
US2736171A (en) * | 1956-02-28 | stalker | ||
US2759663A (en) * | 1953-01-12 | 1956-08-21 | Stalker Dev Company | Slotted compressor blades |
US2825532A (en) * | 1951-01-04 | 1958-03-04 | Snecma | Device for controlling the flow of fluid between cambered blades |
US2831629A (en) * | 1952-05-06 | 1958-04-22 | Westinghouse Electric Corp | Compressor apparatus |
US2859910A (en) * | 1954-03-29 | 1958-11-11 | Edward A Stalker | Stators for axial flow compressors |
US2887957A (en) * | 1953-05-29 | 1959-05-26 | Stalker Corp | Bladed axial flow pump construction |
US2888803A (en) * | 1954-08-30 | 1959-06-02 | Pon Lemuel | Intermittent combustion turbine engine |
US2933238A (en) * | 1954-06-24 | 1960-04-19 | Edward A Stalker | Axial flow compressors incorporating boundary layer control |
US2933236A (en) * | 1955-12-09 | 1960-04-19 | Power Jets Res & Dev Ltd | Rotary dynamic compressors |
US2935246A (en) * | 1949-06-02 | 1960-05-03 | Onera (Off Nat Aerospatiale) | Shock wave compressors, especially for use in connection with continuous flow engines for aircraft |
US2935245A (en) * | 1956-12-10 | 1960-05-03 | Westinghouse Electric Corp | Gas reaction rotors |
US2944729A (en) * | 1957-03-29 | 1960-07-12 | United Aircraft Corp | Induction and discharge means for effective camber control |
US2958456A (en) * | 1954-10-06 | 1960-11-01 | Power Jets Res & Dev Ltd | Multi-stage aerofoil-bladed compressors |
US2966028A (en) * | 1947-10-17 | 1960-12-27 | Gen Electric | Aerodynamic diffuser mechanisms |
US3032313A (en) * | 1956-04-09 | 1962-05-01 | Bertin & Cie | Turbo-machines |
US3237850A (en) * | 1964-08-24 | 1966-03-01 | Borg Warner | Axial flow fan with boundary layer control |
US3365124A (en) * | 1966-02-21 | 1968-01-23 | Gen Electric | Compressor structure |
US3387647A (en) * | 1966-08-15 | 1968-06-11 | Heskestad Gunnar | Air treating means including an air flow directing system |
US3409968A (en) * | 1966-10-03 | 1968-11-12 | Borg Warner | Method of making a slotted blade by extruding |
DE1301432B (en) * | 1965-12-16 | 1969-08-21 | Bbc Brown Boveri & Cie | Arrangement to enlarge the stable working area of single and multi-stage axial compressors, blowers, fans and pumps by means of boundary layer removal |
US6260349B1 (en) | 2000-03-17 | 2001-07-17 | Kenneth F. Griffiths | Multi-stage turbo-machines with specific blade dimension ratios |
US6378287B2 (en) | 2000-03-17 | 2002-04-30 | Kenneth F. Griffiths | Multi-stage turbomachine and design method |
CN108661953A (en) * | 2017-03-28 | 2018-10-16 | 中国科学院工程热物理研究所 | The multi stage axial flow compressor of self-loopa suction jet between stator blade |
-
1943
- 1943-08-07 US US497762A patent/US2344835A/en not_active Expired - Lifetime
Cited By (38)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2736171A (en) * | 1956-02-28 | stalker | ||
US2418801A (en) * | 1942-03-25 | 1947-04-08 | Vickers Electrical Co Ltd | Internal-combustion turbine plant |
US2520697A (en) * | 1943-10-11 | 1950-08-29 | Vickers Electrical Co Ltd | Internal-combustion turbine plant |
US2418221A (en) * | 1944-10-30 | 1947-04-01 | Curtis Pump Co | Liquid and vapor separating pump |
US2656096A (en) * | 1946-01-04 | 1953-10-20 | Rateau Soc | Centrifugal pump and compressor |
US2613028A (en) * | 1946-01-08 | 1952-10-07 | Rolls Royce | Air compressor for use on aircraft |
US2527971A (en) * | 1946-05-15 | 1950-10-31 | Edward A Stalker | Axial-flow compressor |
US2647366A (en) * | 1946-06-24 | 1953-08-04 | William J Mccann | Means for preventing ice formation in jet propulsion and gas turbine engines |
US2597510A (en) * | 1947-04-15 | 1952-05-20 | Worthington Pump & Mach Corp | Blade element for rotary fluid machines |
US2966028A (en) * | 1947-10-17 | 1960-12-27 | Gen Electric | Aerodynamic diffuser mechanisms |
US2501614A (en) * | 1947-11-28 | 1950-03-21 | Lockheed Aircraft Corp | Compressor construction |
US2637487A (en) * | 1948-03-09 | 1953-05-05 | James G Sawyer | Blower |
US2685405A (en) * | 1948-05-03 | 1954-08-03 | Edward A Stalker | Axial flow compressor |
US2698129A (en) * | 1949-05-12 | 1954-12-28 | Joy Mfg Co | Multistage axial fan with boundary layer control |
US2935246A (en) * | 1949-06-02 | 1960-05-03 | Onera (Off Nat Aerospatiale) | Shock wave compressors, especially for use in connection with continuous flow engines for aircraft |
US2682363A (en) * | 1950-12-08 | 1954-06-29 | Rolls Royce | Gas turbine engine |
US2825532A (en) * | 1951-01-04 | 1958-03-04 | Snecma | Device for controlling the flow of fluid between cambered blades |
US2709337A (en) * | 1952-03-28 | 1955-05-31 | United Aircraft Corp | Boundary layer control for the diffuser of a gas turbine |
US2831629A (en) * | 1952-05-06 | 1958-04-22 | Westinghouse Electric Corp | Compressor apparatus |
US2720356A (en) * | 1952-06-12 | 1955-10-11 | John R Erwin | Continuous boundary layer control in compressors |
US2759663A (en) * | 1953-01-12 | 1956-08-21 | Stalker Dev Company | Slotted compressor blades |
US2887957A (en) * | 1953-05-29 | 1959-05-26 | Stalker Corp | Bladed axial flow pump construction |
US2859910A (en) * | 1954-03-29 | 1958-11-11 | Edward A Stalker | Stators for axial flow compressors |
US2933238A (en) * | 1954-06-24 | 1960-04-19 | Edward A Stalker | Axial flow compressors incorporating boundary layer control |
US2888803A (en) * | 1954-08-30 | 1959-06-02 | Pon Lemuel | Intermittent combustion turbine engine |
US2958456A (en) * | 1954-10-06 | 1960-11-01 | Power Jets Res & Dev Ltd | Multi-stage aerofoil-bladed compressors |
US2933236A (en) * | 1955-12-09 | 1960-04-19 | Power Jets Res & Dev Ltd | Rotary dynamic compressors |
US3032313A (en) * | 1956-04-09 | 1962-05-01 | Bertin & Cie | Turbo-machines |
US2935245A (en) * | 1956-12-10 | 1960-05-03 | Westinghouse Electric Corp | Gas reaction rotors |
US2944729A (en) * | 1957-03-29 | 1960-07-12 | United Aircraft Corp | Induction and discharge means for effective camber control |
US3237850A (en) * | 1964-08-24 | 1966-03-01 | Borg Warner | Axial flow fan with boundary layer control |
DE1301432B (en) * | 1965-12-16 | 1969-08-21 | Bbc Brown Boveri & Cie | Arrangement to enlarge the stable working area of single and multi-stage axial compressors, blowers, fans and pumps by means of boundary layer removal |
US3365124A (en) * | 1966-02-21 | 1968-01-23 | Gen Electric | Compressor structure |
US3387647A (en) * | 1966-08-15 | 1968-06-11 | Heskestad Gunnar | Air treating means including an air flow directing system |
US3409968A (en) * | 1966-10-03 | 1968-11-12 | Borg Warner | Method of making a slotted blade by extruding |
US6260349B1 (en) | 2000-03-17 | 2001-07-17 | Kenneth F. Griffiths | Multi-stage turbo-machines with specific blade dimension ratios |
US6378287B2 (en) | 2000-03-17 | 2002-04-30 | Kenneth F. Griffiths | Multi-stage turbomachine and design method |
CN108661953A (en) * | 2017-03-28 | 2018-10-16 | 中国科学院工程热物理研究所 | The multi stage axial flow compressor of self-loopa suction jet between stator blade |
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