US3012709A - Blade for axial compressors - Google Patents

Blade for axial compressors Download PDF

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Publication number
US3012709A
US3012709A US584701A US58470156A US3012709A US 3012709 A US3012709 A US 3012709A US 584701 A US584701 A US 584701A US 58470156 A US58470156 A US 58470156A US 3012709 A US3012709 A US 3012709A
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Prior art keywords
blade
collar
boundary layer
flow
axial
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Expired - Lifetime
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US584701A
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Erwin B G Schnell
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Daimler Benz AG
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Daimler Benz AG
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/26Rotors specially for elastic fluids
    • F04D29/32Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324Blades
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12Blades
    • F01D5/14Form or construction
    • F01D5/141Shape, i.e. outer, aerodynamic form
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/66Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps

Description

1961 E. B. G. SCHNELL 3,012,709

BLADE FOR AXIAL COMPRESSORS Filed May 14, 1956 ERWIN B. G. SCHNELL BY nd/ ATTORNEY J i v 5 2 l 6 l INVENTOR United States Patent Ofifice 3,012,709 Patented Dem-12, 19.61.

3,912,709 BLADE FUR AXIAL COMPRESSORS Erwin B. G. Schnell, Stuttgart-Rohracirer, Germany, as-

signor to Daimler-Benz Aktiengeseilschaft, Stuttgart- Unterturkheirn, Germany Filed May 14, B56, Scr. No. 584,701 Claims priority, application Germany May 18, 1955 5 Claims. (Cl. 23l134) Still another object of the resent invention is to provide a sturdy blade for axial type compressors which have the aforementioned advantageous operating characteristics and which are relatively simple in structure, i.e., which combine these advantageous operating characteristics with relatively light Weight and good rigidity.

In the attempt to render axial compressors suitable for very high flow velocities or rotational speeds the present invention provides a swept-back blade construction, i.e., a blade construction in which the leading or entering edge of the blade is not perpendicular or nearly perpendicular to the longitudinal axis of the device but is inclined rearwardly in the direction of. flow. Such blades exhibit still a. high degree of efficiency even with large axial flow velocities which approach the speed of sound and consequently ordinarily would result in poor efliciency. This is due to the fact that only the components of flow which are perpendicular to the leading or entering edge of the blade are of significance in that case and the same are considerably smaller with a swept-back blade form than is the amount of the axial flow.

Blades are known in the priorart in which the leading or entering edges thereof deviate by a slight angular amount from the perpendicular to the longitudinal axis of the device or machines. However, this angular amount is so small that it does not possess any significant influence on the reduction of the components of how which are perpendicular to the leading or entering edge of the blade. Accordingly, the angular deviation of the prior art devices or machines has no functional reason as regards flow conditions but rest solely on the fact that the blades are made somewhat smaller at the outer ends or tips than at the foot or root thereof only for reasons of rigidity.

Boundary layer regions are produced around the blade as a result of the viscosity of the flow medium during the flow through an axial blade wheel in which the flow velocities decrease from the value of free or unobstructed flow to zero along the blade surface. The particles contained in these boundary layers are, therefore, subjected to a centrifugal acceleration as a result of the rotation of the blade wheel whichproduees a secondary flow effect along the blade surface which is directed outwardly. This phenomena is known as boundary layer centrifuging effect and brings about a removal or withdrawal of the boundary layer material or mass in a manner similar or analogous to the. boundary layersuction from the parts of the lades near the hubthereof'and an accumulation or build-up of boundary. layer material or mass near the outer rims or tipsof the blades. The permissive load on the bladesis the greater the thinner the boundary layer is,

expressed by the maximum lift coefficient c, or by the permissive deceleration of the flow velocity in a cascade or row of blades, which if exceeded would result in break or collapse of the flow and produce pumping which would take place. As a result of the boundary layer centrifuging effect the permissive deceleration is larger in the blade sections nearer the hub than in the outer sections thereof. It follows therefrom that the breaking or collapse or flow or resulting pumping of an axial compressor, or possibly also of an axial turbine, is influenced by the boundary layer movement or transport as a result of secondary flows whereby the thickness of the boundary layer in the outer blade section is decisive. The pumping limit or boundary may therefore be pushed out or be extended considerably if the boundary layer centrifuging effect is interrupted as is possible, in principle, by the provision of a collar arranged at a constant distance from the main axis of the device or machine which is efiective as a boundary layer fence. 7

In swept-back type blades according to the present invention the provision of such boundary layer fences are of particular significance because with such types of blades a boundary layer flow toward the outside which is required aerodynamically and which is caused by the swept-back" shape superimposes itself on the boundary layer centrifuging effect brought about by the rotation of the blades. The result is an extraordinary large increase of the boundary layer in the outer regions of the blades and therewith an increased danger of breaking or collapse of the flow or of pumping respectively.

The present invention is predicated on the discovery that it has proven itself advantageous to provide a collar having a height of approximately one-half the thickness of the blade profile or cross section.- Relatively small collar heights result from such a construction which permit, the use of the boundary layer fences also with relatively large rotational speeds of the runner wheel, the more so, as the boundary layer fence by reason of its arrangement itself rotates only with moderate speeds. As the flow breaks or collapses primarily along the suctionside or upper side of the blade it is important to impede the boundary layer centrifuging effect thereat in an especially effective manner. It may, therefore, be advantageous if the collar height is larger on the blade suction side than on the blade pressure side, or in the alternative if the collar is provided only along the blade suction side. In that manner a sufiicient effectiveness is combined with a relatively light weight construction. If considerations of Weight-saving, on the one hand, and effectiveness on the other are of great importance,

the present invention provides an embodiment in which the collar extends only along a part of the periphery of the blade profile or cross section, especially along onehalf to two-thirds of the profile length with reference to the leading or entering edge of the blade.

Further objects, features and advantages of the present invention will become obvious from the descriptionwhen taken in connection with the accompanying drawingwhich shows, for purposes of illustration only, several embodiments in accordance with the; present invention, and wherein:

FIGURE 1 is a side view of a blade in accordance with the present invention.

. FIGURE 2 is a cross sectional, view of this;blade. taken along line IIII of FIGURE 1'. 7

FIGURE 3 isa cross sectional view through the blade.

of FIGURE 1 taken along line Ill-III thereof andshowing only collar portions. on each side of the blade. FIGURE 4 is a cross sectional View taken alongline IVIV of FIGURE 1' showing a collar portion only along the upper or suction side of the blade, and

FIGURE 5 is a cross sectional view similarto FIGURE 3 of a modified embodiment in which the collar extends around the entire blade profile.

In all the figures the rotary movement in the circumferential direction is indicated by arrow A, whereas the arrows B indicate the direction of flow.

Referring now more particularly to the drawing wherein like reference numerals are used throughout the various views to designate like parts, FIGURES 1 and 2 show a swept-back blade, the leading or entering edge 1 and also the trailing edge 2 of which are inclined rearwardly in the direction of flow B. Two boundary layer fences or collars 3 and 4 are arranged on the blade one behind the other in the radial direction thereof of which the inner one, designated by reference numeral 3 may be constructed as shown in FIGURE 3 which extends along the blade suction side 5 over about two-thirds of the blade width whereas on the blade pressure side 6 the collar extends over about one-half of the blade width taking the leading edge 1 as point of reference. The second fence or collar 4 may be constructed as shown in FIGURE 4 and extends only along the blade suction side 5.

In the embodiment according to FIGURE 3 in the interest of reduction of weight the boundary layer fence or collar is concentrated only in those portions of the blade which are particularly sensitive with respect to the boundary layer displacement.

FIGURE 4 shows an embodiment of a boundary layer fence or collar in which particular importance is attributed to the small weight thereof and which in consideration of the centrifugal forces is, therefore, very advantageous as regards rigidity. Moreover, this embodiment essentially also does not require any more space in the longitudinal direction than a blade without a boundary layer fence or collar. The collar is thereby limited only to the area of larger suction, i.e., to the first half of the upper side 5 of the blade.

In the embodiment according to FIGURE 5 the collar 7 which may be substituted for the collar 3 of FIGURES 1 and 2, which is provided on the blade suction side 5 which serves as boundary layer fence has a larger height a than on the lower side 6 Where the height is designated by reference character b. The boundary layer fence thereby extends along the entire blade profile or cross section.

While I have shown in FIGURES l and 2 a specific embodiment of a swept-back blade with two collars 3 and 4 it is understood that the number thereof as well as the particular construction may be varied within the scope of the present invention and in accordance with my disclosure in FIGURES 3 to 5, depending in each case on the particular requirements of the blade. Moreover the heights of the collars in FIGURE 3 may be dimensioned diiferently on the suction and pressure side thereof, in a manner similar to the different heights a and b in FIGURE 5.

While I have shown several preferred embodiments in accordance with the present invention, it is understood that my invention is susceptible of many modifications and changes and I intend to cover all such modifications and changes except as limited by the appended claims.

I claim:

1. In an axial compressor for compressing a fluid medium passing therethrough and having an axis of rotation, a blade extending essentially in a radial direction and including a leading edge and a trailing edge, said leading edge being inclined at a constant angle of inclination in the direction of flow of said fluid medium as it approaches the leading edge of said blade, said blade further including a collar extending essentially perpendicular to said radial direction so as to be efiective as a boundary layer fence, said collar being disposed between the radially outermost tip and the root of said blade and extending essentially at a constant distance from said axis of rotation in the direction of said flow, the flow of fluid medium passing through said compressor producing a low pressure area on one side of the blade and a high pressure area on the other, the trailing edge of said blade being inclined rearwardly at a constant angle relative to the direction of flow of said fluid medium passing through said compressor, said collar comprising a portion disposed on said one side of said blade and a further portion on said other side of said blade, each of said portions being spaced from said trailing edge.

2. In an axial compressor, the combination according to claim 1 wherein said portion disposed on said one side of said blade is spaced a smaller distance from said trailing edge than said portion on said other side.

3. In an axial compressor, the combination according to claim 1, wherein said collar includes a further portion projecting upstream and around said leading edge.

4. In an axial compressor, the combination according to claim 1, wherein said portion disposed on said one side of said blade extends a greater amount than said portion on said other side.

5. An axial compressor for compressing a fluid medium passing therethrough and having an axis of rotation, comprising at least one blade of swept-back construction extending essentially in a radial direction with the leading edge thereof inclined at a constant angle of inclination in the direction of ficw of said fluid medium as it approaches said leading edge, at least one collar extending from said blade essentially perpendicular to said radial direction and disposed between the radially outermost tip of said blade and the root thereof so as to be effective as a boundary layer fence, said collar further extending essentially in an axial direction at an essentially constant distance from said axis of rotation and over at least a portion of the axial width of said blade, the flow of fluid medium passing through said compressor producing a low pressure area on one side of the blade and a high pressure area on the other, said blade being provided with another collar disposed radially outwardly with respect to said first-mentioned collar and extending at least over a portion of the axial width of said blade with reference to said leading edge, both of said collars extending only over a portion of said axial width of said blade, and wherein said firstmentioned collar is provided on both the low pressure and high pressure side of said blade while said secondmentioned collar is provided only along the low pressure side thereof.

References Cited in the file of this patent UNITED STATES PATENTS 170,937 Cook et al Dec. 14, 1875 914,857 Miller Mar. 9, 1909 978,677 Taylor Dec. 13, 1910 1,022,203 Nettle Apr. 2, 1912 1,080,964 Gays Dec. 9, 1913 1,129,934 Wiedling Mar. 2, 1915 1,446,011 Jackson Feb. 20, 1923 1,793,339 Sherer Feb. 17, 1931 1,862,827 Parsons et al June 14, 1932 2,027,050 Leinweber Jan. 7, 1936 2,099,229 Possenheim Nov. 16, 1937 2,110,621 Cohen Mar. 8, 1938 2,150,299 Telfer Mar. 14, 1939 2,359,466 Currie Oct. 3, 1944 2,390,879 Hagen Dec. 11, 1945 2,426,742 Pawlowski Sept. 2, 1947 2,498,170 Meier Feb. 21, 1950 2,524,870 Adamtchik Oct. 10, 1950 2,540,968 Thomas Feb. 6, 1951 2,839,239 Stalker June 17, 1958 FOREIGN PATENTS 11,785 Great Britain of 1911 19,441 Australia Dec. 31, 1934 27,409 Great Britain of 1906 258,376 Italy Apr. 20, 1928 631,231 Great Britain Oct. 29, 1949 693,727 Great Britain July 8, 1953 719,236 Great Britain Dec. 1, 1954 830,627 Germany Feb. 7, 1952

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Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3193185A (en) * 1962-10-29 1965-07-06 Gen Electric Compressor blading
US3365126A (en) * 1965-09-01 1968-01-23 Gen Electric Compressor blade
US3706512A (en) * 1970-11-16 1972-12-19 United Aircraft Canada Compressor blades
US3871791A (en) * 1972-03-09 1975-03-18 Rolls Royce 1971 Ltd Blade for fluid flow machines
JPS5050404U (en) * 1973-09-05 1975-05-16
JPS5018603B1 (en) * 1968-08-13 1975-07-01
US3976396A (en) * 1974-01-07 1976-08-24 Enrico Antogini Device for converting fluid flow into kinetic energy
EP0161559A2 (en) * 1984-05-15 1985-11-21 A. S. Kongsberg Väpenfabrikk Insertably adjustable and angulary adjustable inlet guide vane apparatus for a compressor
US5759073A (en) * 1995-09-04 1998-06-02 Sanshin Kogyo Kabushiki Kaisha Dual propeller system for marine drive
GB2357808A (en) * 1999-11-30 2001-07-04 Mtu Muenchen Gmbh Blade with ribs to optimize vibration behaviour
US20040091361A1 (en) * 2002-11-12 2004-05-13 Wadia Aspi R. Methods and apparatus for reducing flow across compressor airfoil tips
US6779979B1 (en) * 2003-04-23 2004-08-24 General Electric Company Methods and apparatus for structurally supporting airfoil tips
EP1510652A2 (en) * 2003-08-28 2005-03-02 General Electric Company Methods and apparatus for reducing vibrations induced to compressor airfoils
US20070201983A1 (en) * 2006-02-27 2007-08-30 Paolo Arinci Rotor blade for a ninth phase of a compressor
EP1898052A2 (en) * 2006-08-21 2008-03-12 General Electric Company Flared tip turbine blade
US20130170997A1 (en) * 2012-01-03 2013-07-04 General Electric Company Gas Turbine Nozzle with a Flow Fence
US20130323098A1 (en) * 2012-05-31 2013-12-05 Denso Corporation Axial flow blower
US20130330183A1 (en) * 2012-06-08 2013-12-12 General Electric Company Turbine engine and aerodynamic element of turbine engine
US20130330184A1 (en) * 2012-06-08 2013-12-12 General Electric Company Aerodynamic element of turbine engine
CN103711531A (en) * 2012-10-05 2014-04-09 通用电气公司 An exhaust diffuser
US20140241899A1 (en) * 2013-02-25 2014-08-28 Pratt & Whitney Canada Corp. Blade leading edge tip rib
ITCO20130024A1 (en) * 2013-06-13 2014-12-14 Nuovo Pignone Srl Compressor impellers
US10107108B2 (en) 2015-04-29 2018-10-23 General Electric Company Rotor blade having a flared tip
JP2018178986A (en) * 2017-04-18 2018-11-15 斗山重工業株式会社 Exhaust diffuser having variable type guide vane and gas turbine including the same
EP3441566A1 (en) * 2017-08-08 2019-02-13 Honeywell International Inc. Airfoil with maximum thickness distribution for robustness

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US170937A (en) * 1875-12-14 Improvement in screw-propellers
GB190627409A (en) * 1906-12-01 1907-11-30 Rudolf Pawlikowski Improvements in Steam Turbines.
US914857A (en) * 1908-05-07 1909-03-09 George W Harvey Propeller.
US978677A (en) * 1909-09-10 1910-12-13 David Watson Taylor Screw-propeller.
US1022203A (en) * 1911-07-05 1912-04-02 John F Nettle Propeller.
GB191111785A (en) * 1911-05-16 1912-08-16 Alexander Liwentaal Improvements in or relating to Propellers and the like.
US1080964A (en) * 1912-11-13 1913-12-09 Giuseppe Gays Propeller.
US1129934A (en) * 1908-06-12 1915-03-02 Wiedling Mfg Company Propeller.
US1446011A (en) * 1921-07-05 1923-02-20 Jackson Robert Cattley Propeller
US1793339A (en) * 1929-12-11 1931-02-17 Roberts Brothers Propeller
US1862827A (en) * 1930-01-22 1932-06-14 Parsons Steam turbine
AU1944134A (en) * 1934-09-25 1934-12-31 Buckingham Edwin Improvements in propelling screws
US2027050A (en) * 1933-04-19 1936-01-07 William H Leinweber Fluid operating propeller
US2099229A (en) * 1936-01-15 1937-11-16 Possenheim Louis Fin equipped rudder
US2110621A (en) * 1935-02-08 1938-03-08 Thermal Units Mfg Company Fan
US2150299A (en) * 1937-10-11 1939-03-14 Telfer Edmund Victor Propeller
US2359466A (en) * 1942-07-27 1944-10-03 Gail G Currie Air impeller
US2390879A (en) * 1940-09-21 1945-12-11 B F Sturtevant Co Propeller fan
US2426742A (en) * 1943-11-20 1947-09-02 Felix W Pawlowski Screw propeller
GB631231A (en) * 1947-12-10 1949-10-28 Aerex Ltd Improvements relating to cased screw fans
US2498170A (en) * 1946-06-04 1950-02-21 Meier Gustav Propeller blades
US2524870A (en) * 1944-11-06 1950-10-10 James Russell Kennedy Screw fan, pump, or other cased or uncased screw wheel
US2540968A (en) * 1948-12-23 1951-02-06 Hamilton Thomas Corp Bearing structure for pump shafts
DE830627C (en) * 1949-08-25 1952-02-07 Karl Seifert Dipl Ing Windradfluegel
GB693727A (en) * 1950-01-25 1953-07-08 Power Jets Res & Dev Ltd Improvements relating to bladed rotary fluid-flow machines
GB719236A (en) * 1952-02-06 1954-12-01 English Electric Co Ltd Improvements in and relating to multi-stage axial flow compressors
US2839239A (en) * 1954-06-02 1958-06-17 Edward A Stalker Supersonic axial flow compressors

Patent Citations (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US170937A (en) * 1875-12-14 Improvement in screw-propellers
GB190627409A (en) * 1906-12-01 1907-11-30 Rudolf Pawlikowski Improvements in Steam Turbines.
US914857A (en) * 1908-05-07 1909-03-09 George W Harvey Propeller.
US1129934A (en) * 1908-06-12 1915-03-02 Wiedling Mfg Company Propeller.
US978677A (en) * 1909-09-10 1910-12-13 David Watson Taylor Screw-propeller.
GB191111785A (en) * 1911-05-16 1912-08-16 Alexander Liwentaal Improvements in or relating to Propellers and the like.
US1022203A (en) * 1911-07-05 1912-04-02 John F Nettle Propeller.
US1080964A (en) * 1912-11-13 1913-12-09 Giuseppe Gays Propeller.
US1446011A (en) * 1921-07-05 1923-02-20 Jackson Robert Cattley Propeller
US1793339A (en) * 1929-12-11 1931-02-17 Roberts Brothers Propeller
US1862827A (en) * 1930-01-22 1932-06-14 Parsons Steam turbine
US2027050A (en) * 1933-04-19 1936-01-07 William H Leinweber Fluid operating propeller
AU1944134A (en) * 1934-09-25 1934-12-31 Buckingham Edwin Improvements in propelling screws
US2110621A (en) * 1935-02-08 1938-03-08 Thermal Units Mfg Company Fan
US2099229A (en) * 1936-01-15 1937-11-16 Possenheim Louis Fin equipped rudder
US2150299A (en) * 1937-10-11 1939-03-14 Telfer Edmund Victor Propeller
US2390879A (en) * 1940-09-21 1945-12-11 B F Sturtevant Co Propeller fan
US2359466A (en) * 1942-07-27 1944-10-03 Gail G Currie Air impeller
US2426742A (en) * 1943-11-20 1947-09-02 Felix W Pawlowski Screw propeller
US2524870A (en) * 1944-11-06 1950-10-10 James Russell Kennedy Screw fan, pump, or other cased or uncased screw wheel
US2498170A (en) * 1946-06-04 1950-02-21 Meier Gustav Propeller blades
GB631231A (en) * 1947-12-10 1949-10-28 Aerex Ltd Improvements relating to cased screw fans
US2540968A (en) * 1948-12-23 1951-02-06 Hamilton Thomas Corp Bearing structure for pump shafts
DE830627C (en) * 1949-08-25 1952-02-07 Karl Seifert Dipl Ing Windradfluegel
GB693727A (en) * 1950-01-25 1953-07-08 Power Jets Res & Dev Ltd Improvements relating to bladed rotary fluid-flow machines
GB719236A (en) * 1952-02-06 1954-12-01 English Electric Co Ltd Improvements in and relating to multi-stage axial flow compressors
US2839239A (en) * 1954-06-02 1958-06-17 Edward A Stalker Supersonic axial flow compressors

Cited By (54)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3193185A (en) * 1962-10-29 1965-07-06 Gen Electric Compressor blading
US3365126A (en) * 1965-09-01 1968-01-23 Gen Electric Compressor blade
JPS5018603B1 (en) * 1968-08-13 1975-07-01
US3706512A (en) * 1970-11-16 1972-12-19 United Aircraft Canada Compressor blades
US3871791A (en) * 1972-03-09 1975-03-18 Rolls Royce 1971 Ltd Blade for fluid flow machines
JPS5050404U (en) * 1973-09-05 1975-05-16
US3976396A (en) * 1974-01-07 1976-08-24 Enrico Antogini Device for converting fluid flow into kinetic energy
EP0161559A2 (en) * 1984-05-15 1985-11-21 A. S. Kongsberg Väpenfabrikk Insertably adjustable and angulary adjustable inlet guide vane apparatus for a compressor
EP0161559A3 (en) * 1984-05-15 1987-05-13 A. S. Kongsberg Väpenfabrikk Insertably adjustable and angulary adjustable inlet guide vane apparatus for a compressor
US5759073A (en) * 1995-09-04 1998-06-02 Sanshin Kogyo Kabushiki Kaisha Dual propeller system for marine drive
GB2357808A (en) * 1999-11-30 2001-07-04 Mtu Muenchen Gmbh Blade with ribs to optimize vibration behaviour
US6503053B2 (en) 1999-11-30 2003-01-07 MTU Motoren-und Turbinen München GmbH Blade with optimized vibration behavior
GB2357808B (en) * 1999-11-30 2003-08-27 Mtu Muenchen Gmbh Blade with optimized vibration behaviour
EP1426555A3 (en) * 2002-11-12 2006-07-26 General Electric Company Method and apparatus for reducing flow across compressor airfoil tips
US20040091361A1 (en) * 2002-11-12 2004-05-13 Wadia Aspi R. Methods and apparatus for reducing flow across compressor airfoil tips
US7270519B2 (en) * 2002-11-12 2007-09-18 General Electric Company Methods and apparatus for reducing flow across compressor airfoil tips
CN100554647C (en) 2002-11-12 2009-10-28 通用电气公司 Method and apparatus for reducing flow across compressor airfoil tips
JP2004324646A (en) * 2003-04-23 2004-11-18 General Electric Co <Ge> Method and device for supporting tip of airfoil structurally
EP1471209A2 (en) * 2003-04-23 2004-10-27 General Electric Company Apparatus to reduce the vibrations of gas turbine rotor blades
US6779979B1 (en) * 2003-04-23 2004-08-24 General Electric Company Methods and apparatus for structurally supporting airfoil tips
EP1471209A3 (en) * 2003-04-23 2006-07-12 General Electric Company Apparatus to reduce the vibrations of gas turbine rotor blades
CN1598248B (en) 2003-08-28 2010-12-08 通用电气公司 Apparatus for reducing vibrations induced to compressor airfoils
US6905309B2 (en) * 2003-08-28 2005-06-14 General Electric Company Methods and apparatus for reducing vibrations induced to compressor airfoils
JP2005076634A (en) * 2003-08-28 2005-03-24 General Electric Co <Ge> Method and device for reducing vibration induced to compressor airfoil
EP1510652A2 (en) * 2003-08-28 2005-03-02 General Electric Company Methods and apparatus for reducing vibrations induced to compressor airfoils
EP1510652A3 (en) * 2003-08-28 2012-08-08 General Electric Company Methods and apparatus for reducing vibrations induced to compressor airfoils
US20080044288A1 (en) * 2006-02-27 2008-02-21 Alessio Novori Rotor blade for a second phase of a compressor
US20070201983A1 (en) * 2006-02-27 2007-08-30 Paolo Arinci Rotor blade for a ninth phase of a compressor
US7785074B2 (en) * 2006-02-27 2010-08-31 General Electric Company Rotor blade for a second stage of a compressor
US7766624B2 (en) * 2006-02-27 2010-08-03 Nuovo Pignone S.P.A. Rotor blade for a ninth phase of a compressor
US8632311B2 (en) 2006-08-21 2014-01-21 General Electric Company Flared tip turbine blade
EP1898052A3 (en) * 2006-08-21 2012-07-25 General Electric Company Flared tip turbine blade
EP1898052A2 (en) * 2006-08-21 2008-03-12 General Electric Company Flared tip turbine blade
US20100221122A1 (en) * 2006-08-21 2010-09-02 General Electric Company Flared tip turbine blade
US20130170997A1 (en) * 2012-01-03 2013-07-04 General Electric Company Gas Turbine Nozzle with a Flow Fence
US8944774B2 (en) * 2012-01-03 2015-02-03 General Electric Company Gas turbine nozzle with a flow fence
US20130323098A1 (en) * 2012-05-31 2013-12-05 Denso Corporation Axial flow blower
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