GB678085A - Improvements in or relating to compressors and turbines - Google Patents

Improvements in or relating to compressors and turbines

Info

Publication number
GB678085A
GB678085A GB4171/49A GB417149A GB678085A GB 678085 A GB678085 A GB 678085A GB 4171/49 A GB4171/49 A GB 4171/49A GB 417149 A GB417149 A GB 417149A GB 678085 A GB678085 A GB 678085A
Authority
GB
United Kingdom
Prior art keywords
fluid
blade
blades
convex
slot
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
Application number
GB4171/49A
Inventor
Alan Arnold Griffith
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB4171/49A priority Critical patent/GB678085A/en
Publication of GB678085A publication Critical patent/GB678085A/en
Expired legal-status Critical Current

Links

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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F04D29/66—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
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • 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
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection

Abstract

678,085. Boundary layer control. ROLLSROYCE, Ltd. May 15, 1950 [Feb. 15, 1949]. No. 4171/49. Class 4. [Also in Group XXVI] An axial-flow compressor or turbine has blades with convex and concave surfaces and comprises a slot or slots or the like extending chordwise of the blade adjacent to the root or tip or both on the convex side of the aerodynamic surface, through which slot fluid can be sucked away, or through which a jet of air can be blown so as to prevent intrusion of fluid into the boundary layer on the convex surface of the blade. The rotor blades 15 have platforms 16, the surfaces 16a and 16b extending circumferentially from the convex and concave sides of the blades respectively, the surface 16b being stepped above the surface 16a and being cut away at 20 to permit overlapping of the surfaces, a slot being left between the convex side 15a of each blade and the edge 21 of the adjoining surface 16b through which fluid is drawn off into the crescent-shaped recess 23, through the channels 24 into the space between the blade fixing lugs 17. From here the fluid is drawn through the channels 25 and 26 in the lugs 17 and rotor disc flanges 18 respectively and thence through the ports 27 in the rotor spacer rings 14 to the spaces between the discs 13. The stator blades 11 have similar arrangements for drawing off fluid both at the radially outer and inner ends. At the radially outer ends, the stator blade platforms 12 are of parallelogram shape and have portions which overlap, the fluid being drawn off through a slot formed between a platform extension and the convex surface of a blade, through the channels 33 into the spaces between the casing flanges 10a, 10b. At the radially inner ends, the stator blades are spigoted into a shroud annulus 35 and inserts are provided between each pair of blades, fluid being drawn off through a slot between each insert and the convex surface of each blade and thence through the ports 27 into the spaces between the discs 13. Fluid sucked away from blades in a high pressure region of the turbine or compressor may be used for blowing away the boundary layer at a lower pressure region. In the case of hollow rotor blades, fluid sucked away from the root may be caused to flow through the blade and be employed to blow at the tip. Specification 621,544, [Group XXVI], is referred to.
GB4171/49A 1949-02-15 1949-02-15 Improvements in or relating to compressors and turbines Expired GB678085A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB4171/49A GB678085A (en) 1949-02-15 1949-02-15 Improvements in or relating to compressors and turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4171/49A GB678085A (en) 1949-02-15 1949-02-15 Improvements in or relating to compressors and turbines

Publications (1)

Publication Number Publication Date
GB678085A true GB678085A (en) 1952-08-27

Family

ID=9772043

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4171/49A Expired GB678085A (en) 1949-02-15 1949-02-15 Improvements in or relating to compressors and turbines

Country Status (1)

Country Link
GB (1) GB678085A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1026037B (en) * 1952-09-11 1958-03-13 Maschf Augsburg Nuernberg Ag Shroudless rotor blade for axially flown impeller machines
US3575522A (en) * 1968-08-30 1971-04-20 Gen Motors Corp Turbine cooling
FR2682435A1 (en) * 1987-02-25 1993-04-16 Onera (Off Nat Aerospatiale) Method and device for reducing the noise of a subsonic flow
WO1994012765A1 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Rotor blade with cooled integral platform
GB2406139A (en) * 2003-09-19 2005-03-23 Rolls Royce Plc Compressor boundary layer control
GB2407142A (en) * 2003-10-15 2005-04-20 Rolls Royce Plc An arrangement for bleeding the boundary layer from an aircraft engine
US20090208332A1 (en) * 2008-02-19 2009-08-20 United Technologies Corporation LPC exit guide vane and assembly
EP2236748A3 (en) * 2009-04-01 2013-02-20 Rolls-Royce Plc A rotor arrangement for a gas turbine

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1026037B (en) * 1952-09-11 1958-03-13 Maschf Augsburg Nuernberg Ag Shroudless rotor blade for axially flown impeller machines
US3575522A (en) * 1968-08-30 1971-04-20 Gen Motors Corp Turbine cooling
FR2682435A1 (en) * 1987-02-25 1993-04-16 Onera (Off Nat Aerospatiale) Method and device for reducing the noise of a subsonic flow
WO1994012765A1 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Rotor blade with cooled integral platform
GB2406139A (en) * 2003-09-19 2005-03-23 Rolls Royce Plc Compressor boundary layer control
GB2407142A (en) * 2003-10-15 2005-04-20 Rolls Royce Plc An arrangement for bleeding the boundary layer from an aircraft engine
GB2407142B (en) * 2003-10-15 2006-03-01 Rolls Royce Plc An arrangement for bleeding the boundary layer from an aircraft engine
US7200999B2 (en) 2003-10-15 2007-04-10 Rolls-Royce Plc Arrangement for bleeding the boundary layer from an aircraft engine
US20090208332A1 (en) * 2008-02-19 2009-08-20 United Technologies Corporation LPC exit guide vane and assembly
US8511983B2 (en) 2008-02-19 2013-08-20 United Technologies Corporation LPC exit guide vane and assembly
EP2236748A3 (en) * 2009-04-01 2013-02-20 Rolls-Royce Plc A rotor arrangement for a gas turbine

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