US2268929A - Compressor or the like - Google Patents

Compressor or the like Download PDF

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Publication number
US2268929A
US2268929A US287166A US28716639A US2268929A US 2268929 A US2268929 A US 2268929A US 287166 A US287166 A US 287166A US 28716639 A US28716639 A US 28716639A US 2268929 A US2268929 A US 2268929A
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United States
Prior art keywords
paddles
wheel
compressor
stator
ring
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Expired - Lifetime
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US287166A
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English (en)
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Dupont Emile
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Individual
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Individual
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    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/06—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially radially

Definitions

  • the first object of the present invention is to reduce the power required by the compressor byincreasing the efliciency of the latter.
  • the present invention also tends to decrease the heating of the carburated air. before its inlet into the engine cylinders. Then, it becomes possible to increase the compression ratio without any risk of creatingpre-ignition.
  • the invention also has for its object to reduce the angular speed of the compressor impellers, due to the increased efl'iciency.
  • the present invention also tends, further to the reduction of speed of the compressor wheels, to-simplif y or suppress the speed reduction mechanism interposed between the airplane engine and the compressor, and to reduce the quantity of lubricant used.
  • Fig. 1 is a side elevation with one half shown in section of the form of apparatus with two fluid streams arranged in series.
  • wheel 2 is attached to wheel 2, for instance, by means of screws 8 distributed around a circumference next to the hub of the shaft l.
  • the disc 1 contacts wheel 2 on machined bearing surfaces 9 and I0 and further has-a circular groove ll, next to the icircumference of the attaching screws 8, and in which a corresponding rib l2 of the wheel 2 fits.
  • the disc 1 and the wheel 2 are further joined by filled lugs l3 havingradial ribs, next; to the periphery of said wheel 2.
  • the disc 1 hollow in its central part, is closed on itsradial end by means of a light iron sheet plate l4, fixed to the edges of said disc I, by means of screws 15 for example.
  • Fig. 3 represents, on a large scalefa transverse cross-section through the paddles or blades and the parallelograms of the velocities which. characterize the operation of the apparatus,
  • Fig. 4 15a sectional view of one manner for at- Fig. 5 is a sectional view of an alternative manner of attaching a blade
  • Figs. 6 and 7 are respectively front and'sec-. tional views of another way ofattaching the'paddie, in accordance with the invention.
  • Fig. 8 is a schematic'cross-sectionof a modifled form of turbine in accordance with the invention, but having both streams in parallel.
  • impeller or turbo-compressor represented in Figs. 1,2 and 3 is mounted on-a drive shaft l-which may be,-for example, the end of an airplane engineshaft.
  • a wheelv 2 made of a light alloy or any other metal, is fixed on the shaft I, by means of a key land a conical fitting.
  • Said conical fltting is combined witha drive washer Sheld by a stop nut 6 screwed on' the end a r of shaft l and positively secured.
  • a disc I made of a. light alloy, or any other lit) , characteristics of the apparatus power).
  • carry on their outer surface, circular arrays of paddles or blades I6 I 6 I6 for the disc, I and I1 11 .-for the wheel 2, called movable paddles or blades.
  • the outline of said paddles (Fig. 3) I6 H is difierent for different rings, and according to the (speed and
  • the paddles 16 I1 may be made of a light; alloy, brass, or another metal. They may be obtained by the transverse cutting of bars rolled to their outline, along the length of said cut elements. Round or polygonal stems 18 are machined, long' enough to permit the riveting of the paddles on the wheel 2 or the supporting disc I 1 (Fi 4).
  • may also (Figs. 6 and 7) be fitted in the circular grooves 2
  • the paddles maybe hooped at their end with a riveted ring, as shown in Fig. 5.
  • a plate or cheek 24 on a eylindricalbearmg part 23 of the wheel 2 is mounted a plate or cheek 24, made of a light alloy or any other metal, carrying on its internal face radial ribs 25 cast or stamped together with said check or fixed by welding orbrazing.
  • the cheek 24 constitutes the principal part of the stator; it is fixed to the frame 50 or to the case of the engine; it may even be an integral part of said case.
  • annular discharge collector 28 made, for instance, of light iron plate which is connected to the engine inlet.
  • Tight connection between the plate or cheek 24 andthe cylindrical bearing part 23 of the wheel 2 is obtained by means of a rib joint 29 forming a tight packing.
  • the longitudinal play of the whole of the shaft l and wheel 2, with respect to the plate or check 24, must be less than the play between the padclleslli I1 and the wall facing them.
  • the drive shaft I must be held longitudinally in the bearing next to wheel 2, so that the expansion of said shaft I, in the direction perpendicular to the stator, may be as small as possible.
  • Said second plate or cheek 30 of the stator is fixed to the radial ribs 25, for instance with bolts 3
  • Said second check has a slightly conical shape. It carries circular arrays of stationary blades or paddles 3
  • the stator is completed with an external housing or cheek 34 made of a light alloy or another metal, forming ahousing for the stator, and be-- ing fixed at the periphery of the cheek 24, with bolts 35 and concentric fitting 36, for instance.
  • the housing 34 is continued by an axial tube 33 which constitutes an axial 'fiuid connection to outside the casing, and with flange 39, for the connection of the impeller or compressor inlet p pe
  • the housing 34 and the cheeks 2430 constitute the body of the compressor stator.
  • the two stationary paddles nearest to the pe riphery 31 and 3H, are attached by the above sion (or of a groove 4
  • the wall 42 -of the ring 42 is joined to the cheek 24 of the stator by a set of tubes 43, welded, screwed or rolled in the wall 42
  • said tubes 43 pass across the stator plate or check 24 and have a threaded part 44 extending beyond a fiat bearing surface provided on the outer face of the check 24 around the orifice.
  • a nut 45 screwed on the threaded part 44 and bearing against the fiat surface, insures the tightness of the assembly.
  • stator housing 34 may be provided, on its outer surface, with ribs 46 for strengthening same and furthering the cooling of said v housing,
  • the inner cylin drical face of said ring 40 is-provided with One of the wings of the ring 40 is, provided with The gaseous fiuid thus sucked in by the axial pipe 38 of the housing is progressively compressed bythe rings of movable blades l6 IE IS IS on the disc I, then passing between the tubes 43, said fluid is brought back towards the axis of rotation, under the action of the pressure, through the passage between thefirst stator plate or check 24 and the second stator plate or cheek 30, said fluid being then radially guided by the ribs 25.
  • the fluid then passes through the opening near the shaft of the second stator cheek 30 and is directed outwardly in a centrifugal direction into the rings of stationary paddles 3
  • Both faces of the rotor, constituted by the wheel 2 and the disc I, are thus used for obtaining two stages of compression added one to pressure.
  • stator composed of an inlet collector ii near to. the axis, of two conical cheeks 52 52 -carrying the rings of sta- Then, the fluid,
  • the 'rotor is composed of a wheel 54 fixed on the shaft 55 and presenting, on each one of its faces, rings of movable paddles I6 I6 I1 5 l! mutually interstitially positioned or interfoliated between the rings of stationary paddles 31 37 ...3
  • the two streams are conducted on allsides, of the wheel 54 in a symmetrical and centrifugal manner.
  • . projected on a radius may also vary, the height of said paddles and their pitch being however capable of permitting an appropriate guiding of the fluid stream.
  • the efliciency of the compressor of the in ention is about 0.90.-
  • the internal power of 308 kgms, above indicated, corresponds, taking said eflici'ency into account, to an increase in pressure sufficient to restore at the inlet of an engine operating at an altitude of 4000 meters 9. pressure equal to that prevailing at the ground.
  • the apparatus of the'invention also presents the following technical advantages:
  • the internal efliciency of the apparatus is important, it reaches 0.90 while the lmown compressors have an efliciency around 0.70.
  • the compressor. of the invention further permits, as in the known centrifugal compressors,
  • the invention extends, to the impeller devices described, either serving asturbo-compressors,
  • the invention extends to the devices described,
  • the invention is also capable of many applications and, in particular, of the following:
  • I claim' I 1.
  • a substantially flat rotor having on each of its two radial faces a series of concentric mutually spaced ring arrays of rotor impeller blades, a stator comprising a casing surrounding said rotor and having two .inner radial faces each provided with a series of concentric mutually spaced ring arrays of stator impeller blades which are positioned to interstitially occupy the ring spaces between said ring arrays of rotor impeller blades, an axial fluid connection to outside said casing, peripheral fluid connections to outside said casing, said rotor and stator comprising path defining means for .defining a fluid path from said axial connection radially outwardly through a first said series of ring arrays on one rotor face, thence radially'inwardly through a clear channel inside said casing which extends along the inside of the outer wall thereof, and thence radially outwardly through a second said series of ring arrays
  • stator having-two adjacent substantially radial plates one of which forms a part of the external casing and the other of which constitutes one stator inner radial face carrying a series of ring arrays of stator impeller-blades, and said two adjacent stator radial plates forming between them said clear channel.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US287166A 1939-02-03 1939-07-28 Compressor or the like Expired - Lifetime US2268929A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR849795T 1939-02-03

Publications (1)

Publication Number Publication Date
US2268929A true US2268929A (en) 1942-01-06

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US (1) US2268929A (fr)
FR (1) FR849795A (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2418012A (en) * 1943-09-20 1947-03-25 Chester Thomas Impeller for centrifugal apparatus
US2471892A (en) * 1944-02-14 1949-05-31 Lockheed Aircraft Corp Reactive propulsion power plant having radial flow compressor and turbine means
US2762603A (en) * 1951-02-02 1956-09-11 Martin D Larkin Reaction motor, compressor and burner combination
EP0376644A1 (fr) * 1988-12-28 1990-07-04 Ingersoll-Rand Company Turbomachine radiale
WO2005024242A1 (fr) * 2003-09-09 2005-03-17 Dynamic Boosting Systems Limited Rotor de compresseur radial
EP2400156A3 (fr) * 2010-06-28 2014-06-25 Hamilton Sundstrand Corporation Ventilateur centrifuge à plusieurs étages
US20170164710A1 (en) * 2015-12-11 2017-06-15 Dyson Technology Limited Motor and a hair care appliance comprising a motor
US20180163567A1 (en) * 2013-03-14 2018-06-14 John French Multi-stage radial flow turbine

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2418012A (en) * 1943-09-20 1947-03-25 Chester Thomas Impeller for centrifugal apparatus
US2471892A (en) * 1944-02-14 1949-05-31 Lockheed Aircraft Corp Reactive propulsion power plant having radial flow compressor and turbine means
US2762603A (en) * 1951-02-02 1956-09-11 Martin D Larkin Reaction motor, compressor and burner combination
EP0376644A1 (fr) * 1988-12-28 1990-07-04 Ingersoll-Rand Company Turbomachine radiale
WO2005024242A1 (fr) * 2003-09-09 2005-03-17 Dynamic Boosting Systems Limited Rotor de compresseur radial
EP2400156A3 (fr) * 2010-06-28 2014-06-25 Hamilton Sundstrand Corporation Ventilateur centrifuge à plusieurs étages
US20180163567A1 (en) * 2013-03-14 2018-06-14 John French Multi-stage radial flow turbine
US10781720B2 (en) * 2013-03-14 2020-09-22 John French Multi-stage radial flow turbine
US20170164710A1 (en) * 2015-12-11 2017-06-15 Dyson Technology Limited Motor and a hair care appliance comprising a motor
US10064470B2 (en) * 2015-12-11 2018-09-04 Dyson Technology Limited Motor and a hair care appliance comprising a motor

Also Published As

Publication number Publication date
FR849795A (fr) 1939-12-01

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