US3193185A - Compressor blading - Google Patents

Compressor blading Download PDF

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Publication number
US3193185A
US3193185A US233661A US23366162A US3193185A US 3193185 A US3193185 A US 3193185A US 233661 A US233661 A US 233661A US 23366162 A US23366162 A US 23366162A US 3193185 A US3193185 A US 3193185A
Authority
US
United States
Prior art keywords
blade
blades
vane
flow
compressor
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
Application number
US233661A
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English (en)
Inventor
John R Erwin
Jr Leroy H Smith
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority to BE638547D priority Critical patent/BE638547A/xx
Application filed by General Electric Co filed Critical General Electric Co
Priority to US233661A priority patent/US3193185A/en
Priority to FR950478A priority patent/FR1373327A/fr
Priority to CH1293463A priority patent/CH417837A/de
Priority to DE19631428110 priority patent/DE1428110A1/de
Priority to GB42174/63A priority patent/GB996041A/en
Priority to SE11885/63A priority patent/SE307216B/xx
Application granted granted Critical
Publication of US3193185A publication Critical patent/US3193185A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • 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

  • the present invention relates to blading and, more particularly, to compressor blading that has flow augmenting means as an integral part thereof.
  • boundary layer is well known and is found in compressor and turbine operation. While applicable to a turbine, the invention is primarily suited for but not limited to compressors and will bedescribed in connection with compressors. In a typical compressor where wall members are formed by a casing and hub respectively with airfoil blades operating in an annulus between the walls, it is known that boundary layer air tends to adhere to the adjacent Walls. This results in slow moving low energy air at these walls and a tendency to break down the smooth primary airflow to the blades.
  • the main object of the present invention is to provide compressor blading employing means to relocate and/ or energize the boundary layer air.
  • Another object is to provide such blading with an attachment that enables the secondary fiow to be augmented for moving the boundary layer for better mixing and also assist in turning the fluid in the direction resulting in greater energy addition to the low energy boundary layer fluid.
  • a further object is to provide a compressor rotor having blading which, by means of an attachment thereto, promotes mixing and turning of the low energy boundary layer and consequent postponement of compressor stall.
  • the present invention includes a compressor rotor with a hub to form an inner wall member and an outer casing to form an outer wall member with a row of cambered airfoil blades attached to one of the walls and radially extending towards the other wall.
  • An axially-extending air passage is thus formed containing the blades for passage of air therethrough.
  • the blades are equipped with flow directing vane-like means mounted substantially at right angles to each blade and located adjacent one of the Walls.”
  • the vane-like means is oriented on the blades so that the flow passing across the concave pressure surface of the blade is directed by the vane-like means toward the adjacent wall.
  • FIGURE 1 is a partial diagrammatic cross-section of a compressor rotor
  • FIGURE 2 is a partial view of a pair of rotor blades illustrating the cross-flow between the blades
  • FIGURE 3 is a top view taken on the line 33 of FIGURE 2,
  • FIGURE 4 is a view similar to FIGURE 2 showing the addition of the vane-like means adjacent the hub,
  • FIGURE 5 is a similar view showing a diflerent vanelike means adjacent the hub and the tip of the blade and applied to one side only,
  • FIGURE 6 is a partial view of a modification using the vane-like means between the blades.
  • FIGURE 7 is a plot showing the effect of the vanelike means on the stall characteristics of a typical compressor.
  • FIGURE 1 there is shown diagrammatically a compressor rotor having a hub 10 and an outer casing 11. Both of these form inner and outer wall members respectively. Between these, in the conventional manner, the hub 10 carries rows of rotor blades 12 and casing 11 has similar stator blades 13 each extending radially toward the opposite wall. An axially-extending air passage 14 is thus formed in the conventional manner for the flow of air through the compressor to emerge at higher pressure on the right end of the figure.
  • FIGURE 2 showing a pair of rotor blades will illustrate the flow difficulties encountered in a compressor. It should be understood that the discussion of the invention will proceed with respect to the rotor blades for convenience only and that the same reasoning applies to the stator blades. Since the rotor blades are conventionally cambered airfoils having convex pressure and concave suction surfaces as shown in FIGURE 3, there are two airilows that normally occur. The first is the primary airflow which approaches the leading edge of the blades and exits from the trailing edge as shown by the straight arrow in FIGURE 3 and is compressed to a higher pressure in the usual manner. The second flow is called secondary flow and is the motion of the air essentially normal to the main flow or transverse of the passage.
  • the secondary flow as shown by the curved arrows in FIGURE 3, has a significant transverse or cross-passage component whereas the deflection of the main stream of air caused by the blading does not have such a large component.
  • This greater cross-passage or transverse component results in a larger turning and therefore an increased energy addition to the low momentum boundary layer fluid.
  • the secondary flow when viewed in the projection of FIGURE 2, is shown by arrows 15.
  • the secondary flow transports main stream fluid along the concave surface of the blade toward hub 10 and casing 11 within the air passage as shown by the arrows and transports the boundary layer fluid away from the hub and casing into the center portion of the axial passage between adjacent blades along the convex blade surface.
  • the result of both the turning and mixing is that the boundary layers are energizedso that a.higher pressure rise across the compressor blading may be accomplished-without; stall.
  • the instant invention is intended tolaugmentv the turnboundary layer
  • the term adjacent wall is intended to be that wallon which the nearest-boundary layer isfound.
  • vane-like means 16 which may be flat (i.e., zero camber) but are preferably more cambered as shown, are particularly located at rightangles to the blade, whether stator or rotor, so that the main flow pas'sing near the concave promote the mixing the airfoils are provided with flow directing vane- Referring next to FIGURE 6,- a modification is shown I wherein the vane-like means 21 may be attached to the 5 air particle on the concave or plus side of blade 12 would follow the 'path shown by arrow and line 22 as it migrated along the hub toward adjacent blade 12. With vane 12 in place and oriented as shown, the same particle'follows the surface of the blade is directed toward the adjacent wall.
  • blade 12 has a concave surface 17 and a convex surface 18. Since-the main airstreami flow shown by arrow 19 creates-the secondary flow shown in FIGURE 2, due to the blade pressure surfaces,
  • vane means 16 is oriented and cambered on the blade 12 to direct the flow down as shown in FIGURE 4 on the i concave surface across the passage between the bladesand up or radially out as shown on the convex surface" of the adjacent upstream blade;
  • vane-means 16 is oriented substantially at right angles on blade '12 to pro-j mote flow in this direction.
  • the vanes are disposed at a radial location along blade 12 substantially at the surface of the boundary layer of the adjacent wall and-thus adjacent the wall. In FIGURE 4 this locates vane 16 at the surface of the boundary layer on wall or hub 10. This is the root portion of rotor blade 12 as shown in FIGURE 4. Sim
  • vane-like'means 16 may be required on the tip portion of the rotor blade as well.
  • FIGURE ,5 This configuration is shown in FIGURE ,5 wherein an additional vane 20 is provided at the tip of the rotor blade near casing '11. 'T he stall characteristics of the particular rotor blade. It may be unnecessary to provide the vanelike means on both sides of the rotor blade. Additionally, various configurations may be provided. As illustrative, the configuration shown in FIGURE 4 is 'a cambered vane means that extends forward of the leading edge of the blade and the configuration of FIGURE 5 is a cambered arrangement with the vane means extending substantially from the leading edge to thetrailing edge only. This latter permits use in multiplestage com-- pressors without interference. Under-any circumstances, the vane-like means is provided on the concave surface to promote and augment the transverse flow between adjacent blades from the higher pressure concave "surface a to the adjacent upstream blades lower pressure convex suction surface.
  • the vane means may be applied at both the root and tip portions," as shown in FIGURE 5, to directthe'fiowl Since toward the adjacent wall having a boundary-layer.
  • the vane is disposed substantially at-the surfacefof the In other words, the vanes are oriented to augment. the transverse flow.
  • FIGURES illustrates the use of the vane-like means on only one side of the 1 of the vanerlike means permits the stall point of a given path of arrow and line 23 by first: followingthe convex negativeor suctionsurface of vane 21 and onto the convex or suction surface of vane 12. Greater turning is imparted to the particle resulting inmore. energy addition I to the low energy boundary layer, better mixing and augmentation of the secondary transverse flow.
  • FIGURE 7 illustrates'the results of employing the vane-like means wherein it can be seen thatas'the percentage of vanes is increased, a higher pressure rise is obtainable before stall occurs.
  • the use of the vane means changes the conventional pressure profile andbringsin greater velocity gradients totransfer energy more rapidly-from the'mainstream 'to they boundary layer by moving the boundary layer transverselyand promotingmixing and energizing re-' sultingin" a greater pressure rise per compressor stage. While.
  • the vane-like.,.means have been shown as curved or cambered in FIGURE 4 and substantially fiat or near zero camber in FIGURE 5, 'it' is preferable that a more ⁇ cambered version be used since it provides a stronger V in light of the above teachings.
  • a rotor having a hub formingan inner wall member
  • cambered airfoil blade members having convex suction: and concave pressure surfaces and being attached to one of said wall members and extending radially toward the other wall member to form an axially-extending air passage'through said blades whereby a transverse secondary flow from said pres?
  • said vane-like means being oriented and cambered on said blades so that the flow passing near the concave pressure surface of said blade is directed by said vane-like means toward the adjacent wall and convex suction surface of the adjacent upstream blade.
  • a compressor rotor having a hub forming an inner well member
  • a row of cambered airfoil blades having convex suc tion and concave pressure surfaces and being attached to one of said wall members and extending radially toward the other wall member to form an axially-extending air passage through said blades whereby a transverse secondary flow from said pressure surface of each blade to said suction surface of the adjacent upstream 'blade is set up across the air passage between said blades,
  • said vane-like means extending on said blade from substantially the leading to trailing airfoil edge and being cambered and oriented on said blade so that the flow passing near the concave pressure side of said blade is directed by said vane-like means toward the adjacent wall and convex suction surface of the adjacent upstream blade.
  • vanelike means is disposed at both the root and tip portions of the rotor blades to direct flow near the concave side generally inward at the root portion and outward at the tip portion of said blade.
  • said flow directing vane-like means comprises an airfoil member oriented and overcambered beyond said blade members and radially extending from one of said Wall members between said blade members.
US233661A 1962-10-29 1962-10-29 Compressor blading Expired - Lifetime US3193185A (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
BE638547D BE638547A (xx) 1962-10-29
US233661A US3193185A (en) 1962-10-29 1962-10-29 Compressor blading
FR950478A FR1373327A (fr) 1962-10-29 1963-10-14 Structure spéciale de lames pour compresseur ou turbine
CH1293463A CH417837A (de) 1962-10-29 1963-10-22 Hilfsbeschaufelung an Strömungsmaschine
DE19631428110 DE1428110A1 (de) 1962-10-29 1963-10-23 Kompressorbeschaufelung
GB42174/63A GB996041A (en) 1962-10-29 1963-10-25 Improvements in compressor or turbine blading
SE11885/63A SE307216B (xx) 1962-10-29 1963-10-29

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US233661A US3193185A (en) 1962-10-29 1962-10-29 Compressor blading

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US3193185A true US3193185A (en) 1965-07-06

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US233661A Expired - Lifetime US3193185A (en) 1962-10-29 1962-10-29 Compressor blading

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US (1) US3193185A (xx)
BE (1) BE638547A (xx)
CH (1) CH417837A (xx)
DE (1) DE1428110A1 (xx)
GB (1) GB996041A (xx)
SE (1) SE307216B (xx)

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US4116584A (en) * 1973-10-12 1978-09-26 Gutehoffnungshutte Sterkrade Ag Device for extending the working range of axial flow compressors
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US4189281A (en) * 1976-12-20 1980-02-19 Kabushiki Kaisha Toyota Chuo Kenkyusho Axial flow fan having auxiliary blades
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DE3012904A1 (de) * 1979-04-06 1980-10-16 Hitachi Ltd Mit schaufeln versehener diffusor fuer eine stroemungsmaschine
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US20070201983A1 (en) * 2006-02-27 2007-08-30 Paolo Arinci Rotor blade for a ninth phase of a compressor
EP2093378A1 (en) * 2008-02-25 2009-08-26 ALSTOM Technology Ltd Upgrading method for a blade by retrofitting a winglet, and correspondingly upgraded blade
US20100054946A1 (en) * 2008-09-04 2010-03-04 John Orosa Compressor blade with forward sweep and dihedral
US20100163598A1 (en) * 2008-12-23 2010-07-01 Belzer George E Shield for surgical stapler and method of use
US20120269623A1 (en) * 2009-12-16 2012-10-25 Trevor Milne Guide vane with a winglet for an energy converting machine and machine for converting energy comprising the guide vane
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US8591195B2 (en) 2010-05-28 2013-11-26 Pratt & Whitney Canada Corp. Turbine blade with pressure side stiffening rib
US20140191623A1 (en) * 2011-09-12 2014-07-10 Brose Fahrzeugteile Gmbh & Co. Kommanditgesellschaft, Wuerzburg Breathing electric motor
US20140328675A1 (en) * 2013-05-03 2014-11-06 Techspace Aero S.A. Axial Turbomachine Stator with Ailerons at the Blade Roots
US9359900B2 (en) 2012-10-05 2016-06-07 General Electric Company Exhaust diffuser
US20160186772A1 (en) * 2014-12-29 2016-06-30 General Electric Company Axial compressor rotor incorporating non-axisymmetric hub flowpath and splittered blades
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US20160348694A1 (en) * 2015-05-26 2016-12-01 Pratt & Whitney Canada Corp. Gas turbine stator with winglets
US20170184053A1 (en) * 2015-12-23 2017-06-29 Rolls-Royce Plc Gas turbine engine vane splitter
US20170234134A1 (en) * 2016-02-12 2017-08-17 General Electric Company Riblets For A Flowpath Surface Of A Turbomachine
US20180017019A1 (en) * 2016-07-15 2018-01-18 General Electric Company Turbofan engine wth a splittered rotor fan
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US20180216631A1 (en) * 2017-02-01 2018-08-02 Rolls-Royce Plc Geared gas turbine engine
CN110067774A (zh) * 2019-04-16 2019-07-30 中国航发湖南动力机械研究所 组合叶轮及燃气涡轮发动机的压气机
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Also Published As

Publication number Publication date
CH417837A (de) 1966-07-31
SE307216B (xx) 1968-12-23
DE1428110A1 (de) 1969-02-13
BE638547A (xx) 1900-01-01
GB996041A (en) 1965-06-23

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