US1035364A - Elastic-fluid compressor. - Google Patents
Elastic-fluid compressor. Download PDFInfo
- Publication number
- US1035364A US1035364A US66408611A US1911664086A US1035364A US 1035364 A US1035364 A US 1035364A US 66408611 A US66408611 A US 66408611A US 1911664086 A US1911664086 A US 1911664086A US 1035364 A US1035364 A US 1035364A
- Authority
- US
- United States
- Prior art keywords
- blades
- blade
- elastic
- fluid compressor
- threads
- 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
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Classifications
-
- 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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/10—Methods of surface bonding and/or assembly therefor
- Y10T156/1002—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina
- Y10T156/1043—Subsequent to assembly
- Y10T156/1044—Subsequent to assembly of parallel stacked sheets only
Definitions
- MAURICE LEBLANC OF (i110 SSY, FRANCE, ASSIGNOR TO STE AME POUR LEXPLOITA- TION DES PROCED S WESTINGHOUSE LEBLANC, OF PARIS, FRANCE.
- the compressor which forms the object of this invention is composed of several force and associated in series.
- the g'eneral arrangement is similar to that of all apparatus of the kind.
- the novel feature of the invention resides in the construction of the rotors and in particular the constitution of their blades.
- Figure 1 of the accompanying drawings is a longitudinalsection through the compressor.
- Fig. 2 is a transverse section and Fig. 3 a longitudinal section through one of the rotors.
- Fig. 4: is a diagrammatic representation of one of the blades drawn to an enlarged scale and seen in end view, showing that its profile is such that the blade has umforn reslstance.
- Fig. 5 is an end elevation of one of the blades and Fig. 6 is a fragmentary side elevation thereof.
- the blade shown is rectangular, in side elevation. It may have any suitable profile provided that the width of the blade diminishes with the distance from the base and that its thickness decreases.
- the blades constructed according to this invention are made of vegetable fibers, such as hemp, cotton, flax, or preferably ramie, united together by a suitable ag lutinant, such as caoutchouc, balata, lori viscose, gelatin, a resin or a suitable gum.
- a suitable ag lutinant such as caoutchouc, balata, lori viscose, gelatin, a resin or a suitable gum.
- caoutchouc is used for the sake of illustration it may be supposed that caoutchouc is used.
- the blades are made in the following manner :-A cylinder is covered with a helix of very close turns, consisting of a very homogeneously manufactured thread of the selected vegetable fibers, the winding being under tension. The whole is then painted over with a solution of caoutchouc containng sulfur and the cylinder is introduced into a stove for drying the solution and causing the threads to adhere to'each other. This covering is then out along a generatrix of the cylinder and unrolled. In this manner there is obtained a very thin rectangular band composed of rectilinear threads stretched parallel to each other and contiguous with each other (Fig 6). A number of these bands of different length are now folded over an ebonite wedge, such as that shown at 5 in Fig.
- the blades have to turn between two metallic plates a ainst which they may rub.
- the blades keep themselves straight, all their fibers remaining perpendicular to the true axis of rotation under the influence of centrifugal force, the elasticity of the aig glutinant permitting them to move slightly relatively to each other.
- the action of the blades cannot develop any appreciable couple on the nave or on :the shaft which carries it, as would happen if they were metallic.
- the flexibility of the blades dispenses with the use ofa flexible shaft.
Description
,M. LEBLANG.
ELASTIC FLUID COMPRESSOR.
APPLICATION FILED D20. 6, 1011.
Patented Aug. 13, 1912.
(ff/m;
'n c tmw 1 Qua/ a UNITED sTAtrEs PATENT OFFICE.
MAURICE LEBLANC, OF (i110 SSY, FRANCE, ASSIGNOR TO STE AME POUR LEXPLOITA- TION DES PROCED S WESTINGHOUSE LEBLANC, OF PARIS, FRANCE.
ELASTIC-FLUID COMPRESSOR.
Specification of Letters Patent.
Application filed December 5, 1911. Serial No. 664,086.
To all whom it may concern:
Be it known that I, MAURICE LnBLANo, a citizen of the Republic of France, residing in Croissy, Seine-et-Oise, France, have inof several hundred meters per second what- .compressing units operating by centrifugal ever may be their angular speed, which is necessary if the compressor is to be used not only for compressing air taken in at the atmospheric pressure but also for producing and maintaining a high vacuum in an inclosed space.
The compressor which forms the object of this invention is composed of several force and associated in series. The g'eneral arrangement is similar to that of all apparatus of the kind.
The novel feature of the invention resides in the construction of the rotors and in particular the constitution of their blades.
Figure 1 of the accompanying drawings is a longitudinalsection through the compressor. Fig. 2 is a transverse section and Fig. 3 a longitudinal section through one of the rotors. Fig. 4: is a diagrammatic representation of one of the blades drawn to an enlarged scale and seen in end view, showing that its profile is such that the blade has umforn reslstance. Fig. 5 is an end elevation of one of the blades and Fig. 6 is a fragmentary side elevation thereof. The blade shown is rectangular, in side elevation. It may have any suitable profile provided that the width of the blade diminishes with the distance from the base and that its thickness decreases.
' The blade suddenly expands at its base so ery of the nave for the purpose of receiving the heels 2 of the blades. To maintain the blades in place laterally, circular cells (Fig. 3) are provided at the ends of the nave on each si e of the notch receiving the heel. Into these cells are introduced segments 4, 4, which expand, owing to their elasticity, and are held in place during working against the bottom of the cells by centrifugal force. p
The blades constructed according to this invention are made of vegetable fibers, such as hemp, cotton, flax, or preferably ramie, united together by a suitable ag lutinant, such as caoutchouc, balata, lori viscose, gelatin, a resin or a suitable gum. For the sake of illustration it may be supposed that caoutchouc is used.
The blades are made in the following manner :-A cylinder is covered with a helix of very close turns, consisting of a very homogeneously manufactured thread of the selected vegetable fibers, the winding being under tension. The whole is then painted over with a solution of caoutchouc containng sulfur and the cylinder is introduced into a stove for drying the solution and causing the threads to adhere to'each other. This covering is then out along a generatrix of the cylinder and unrolled. In this manner there is obtained a very thin rectangular band composed of rectilinear threads stretched parallel to each other and contiguous with each other (Fig 6). A number of these bands of different length are now folded over an ebonite wedge, such as that shown at 5 in Fig. 5, the arrangement being such that the super-position of the bands forms a body having substantially a profile of uniform resistance. The assemblage of bands is now introduced into a two part mold, the internal surface of which is stepped so as to follow the form of the blade, and is forcibly pressed therein. The mold is then introduced into the vulcanizing stove. When vulcanization is complete .it only remains to remove the blade from the mold. There are thus obtained ebonite blades strengthened by vegetable fibers in the direction of their length but not in the direction of their width. Every precaution should be taken that in the course of the Patented Aug. 13, 1912.
manufacture, the mass of agglutinant used Iio The mode of manufacture described above is given only by wayof example; it may be varied notably with the nature of the agglutinantiselected and with the treatment which" determines the selection.
The blades thus made present the following advantages:
1. Their density is close to that of water. The tenacity of the vegetable fibers is sufli-- ciently great to enable them to resist centrifugal force better than the. fibers of steel which are seven to eight times as dense. This is a known fact, witness the manufactureof aeroplane propellers ofwood instead of metal, owing to the high peripheral angular speeds that they are to attain. This result would not be obtained if the blades were made of bands of cloth in which the threads of the warp were stretched in the direction of their length. The threads of the weft would increase the mass of the blade without adding anything to its resistance in the longitudinal direction. They would 1 give it, it is true, high resistance in the. transverse direction, but that is useless, since the blade has no strain to support in this direction.
2. These blades do not sufi'er appreciably more elongation under the influence of centrifugal force than metallic blades of the same profile do. Moreover, they do not become deformed. This is because the threads have been stretched beforehand and could only become longer if the constituent fibers were themselves to be extended; On the other hand in a cloth fabric the threads are engaged with each other and have a wavy form. When a band of cloth is stretched in the direction of the warp for example the threads of the 'latter first straighten themselves and are much extended before the constituent fibers are appreciably extended. During this time the waviness of the weft threads is increased and the blade is deformed.
3. The blades have to turn between two metallic plates a ainst which they may rub.
without injuring" hem. The bladeswear at their edges, being ground to powder, which is immediately thrown outwardlywuntil the friction ceases. If the blades were of metal each rotor would actas a cutter on the plates and would soon put them out of use. Thus the blades may be a little too wide in the first instance and may be turned between the plates at a reduced speed for the purpose of wearing them. The most simple arrangement is to have only extremely small play, this being allowable only in compressors of low power.
4. The blades keep themselves straight, all their fibers remaining perpendicular to the true axis of rotation under the influence of centrifugal force, the elasticity of the aig glutinant permitting them to move slightly relatively to each other. The action of the blades cannot develop any appreciable couple on the nave or on :the shaft which carries it, as would happen if they were metallic. The flexibility of the blades dispenses with the use ofa flexible shaft.
Having thus described my invention and the best means I know of carrying the same.
into practical effect, I claim 1. In a rotary elastic fluid compressor, blades composed of vegetable fibers stretched parallel to each other radially to the rotor and united together by a suitable agglutinant, substantially as described.
2. In a rotary elastic fluid compressor, blades composed of fibrous material extended longitudinally of the blade and united by an agglutinant. I,
In witness whereof, I have hereunto signed my name in the presence of two subscribing witnesses.
MAURICE LEBLANC.
Witnesses:
Jonas ARMENGAUD, Jeune, 1F ERNAND BARRF'J.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US66408611A US1035364A (en) | 1911-12-05 | 1911-12-05 | Elastic-fluid compressor. |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US66408611A US1035364A (en) | 1911-12-05 | 1911-12-05 | Elastic-fluid compressor. |
Publications (1)
Publication Number | Publication Date |
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US1035364A true US1035364A (en) | 1912-08-13 |
Family
ID=3103644
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Application Number | Title | Priority Date | Filing Date |
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US66408611A Expired - Lifetime US1035364A (en) | 1911-12-05 | 1911-12-05 | Elastic-fluid compressor. |
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Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2656146A (en) * | 1948-04-08 | 1953-10-20 | Curtiss Wright Corp | Turbine blade construction |
US2796215A (en) * | 1952-08-19 | 1957-06-18 | Cincinnati Testing & Res Lab | Compressor blade and method of making |
US2859936A (en) * | 1954-03-03 | 1958-11-11 | Cincinnati Testing & Res Lab | Compressor blade and method of forming same |
US2861775A (en) * | 1953-06-04 | 1958-11-25 | Power Jets Res & Dev Ltd | Tubular blades |
US2868441A (en) * | 1954-02-24 | 1959-01-13 | Armstrong Siddeley Motors Ltd | Plastic blades, particularly for a compressor rotor of a gas turbine engine |
US2868439A (en) * | 1954-05-07 | 1959-01-13 | Goodyear Aircraft Corp | Plastic axial-flow compressor for gas turbines |
US2870959A (en) * | 1956-11-07 | 1959-01-27 | Amana Refrigeration Inc | Blower wheel |
US2919889A (en) * | 1955-03-03 | 1960-01-05 | United Aircraft Corp | Blade mounting |
US2934317A (en) * | 1954-05-05 | 1960-04-26 | Studebaker Packard Corp | Prestressed compressor blade |
US2937805A (en) * | 1952-12-15 | 1960-05-24 | Studebaker Packard Corp | Stator blade assembly and method and machine for making same |
US2950083A (en) * | 1954-07-23 | 1960-08-23 | Thompson Ramo Wooldridge Inc | Blade assembly |
US2997847A (en) * | 1957-12-20 | 1961-08-29 | Hollingsworth R Lee | Combustion engines for rockets and aeroplanes |
US3132841A (en) * | 1958-05-12 | 1964-05-12 | Gen Motors Corp | Compressor blade and manufacture thereof |
US3178101A (en) * | 1961-04-27 | 1965-04-13 | Rolls Royce | Axial flow compressors |
US3202343A (en) * | 1962-05-16 | 1965-08-24 | Desalination Plants | Compressor arrangement |
US3255514A (en) * | 1962-05-16 | 1966-06-14 | Desalination Plants | Method of fabricating rotor assemblies |
US3255602A (en) * | 1964-07-08 | 1966-06-14 | Desalination Plants | Compressor construction |
US3574477A (en) * | 1969-02-19 | 1971-04-13 | Boeing Co | Noise attenuating system for rotary engines |
US4547126A (en) * | 1983-12-08 | 1985-10-15 | Jackson Samuel G | Fan impeller with flexible blades |
US20190162201A1 (en) * | 2017-11-24 | 2019-05-30 | Pegatron Corporation | Impeller, fan and method for manufacturing fan blade |
-
1911
- 1911-12-05 US US66408611A patent/US1035364A/en not_active Expired - Lifetime
Cited By (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2656146A (en) * | 1948-04-08 | 1953-10-20 | Curtiss Wright Corp | Turbine blade construction |
US2796215A (en) * | 1952-08-19 | 1957-06-18 | Cincinnati Testing & Res Lab | Compressor blade and method of making |
US2937805A (en) * | 1952-12-15 | 1960-05-24 | Studebaker Packard Corp | Stator blade assembly and method and machine for making same |
US2861775A (en) * | 1953-06-04 | 1958-11-25 | Power Jets Res & Dev Ltd | Tubular blades |
US2868441A (en) * | 1954-02-24 | 1959-01-13 | Armstrong Siddeley Motors Ltd | Plastic blades, particularly for a compressor rotor of a gas turbine engine |
US2859936A (en) * | 1954-03-03 | 1958-11-11 | Cincinnati Testing & Res Lab | Compressor blade and method of forming same |
US2934317A (en) * | 1954-05-05 | 1960-04-26 | Studebaker Packard Corp | Prestressed compressor blade |
US2868439A (en) * | 1954-05-07 | 1959-01-13 | Goodyear Aircraft Corp | Plastic axial-flow compressor for gas turbines |
US2950083A (en) * | 1954-07-23 | 1960-08-23 | Thompson Ramo Wooldridge Inc | Blade assembly |
US2919889A (en) * | 1955-03-03 | 1960-01-05 | United Aircraft Corp | Blade mounting |
US2870959A (en) * | 1956-11-07 | 1959-01-27 | Amana Refrigeration Inc | Blower wheel |
US2997847A (en) * | 1957-12-20 | 1961-08-29 | Hollingsworth R Lee | Combustion engines for rockets and aeroplanes |
US3132841A (en) * | 1958-05-12 | 1964-05-12 | Gen Motors Corp | Compressor blade and manufacture thereof |
US3178101A (en) * | 1961-04-27 | 1965-04-13 | Rolls Royce | Axial flow compressors |
US3202343A (en) * | 1962-05-16 | 1965-08-24 | Desalination Plants | Compressor arrangement |
US3255514A (en) * | 1962-05-16 | 1966-06-14 | Desalination Plants | Method of fabricating rotor assemblies |
US3255602A (en) * | 1964-07-08 | 1966-06-14 | Desalination Plants | Compressor construction |
US3574477A (en) * | 1969-02-19 | 1971-04-13 | Boeing Co | Noise attenuating system for rotary engines |
US4547126A (en) * | 1983-12-08 | 1985-10-15 | Jackson Samuel G | Fan impeller with flexible blades |
US20190162201A1 (en) * | 2017-11-24 | 2019-05-30 | Pegatron Corporation | Impeller, fan and method for manufacturing fan blade |
US10794393B2 (en) * | 2017-11-24 | 2020-10-06 | Pegatron Corporation | Impeller, fan and method for manufacturing fan blade |
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