US3051440A - Air driven turbines - Google Patents

Air driven turbines Download PDF

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Publication number
US3051440A
US3051440A US44179A US4417960A US3051440A US 3051440 A US3051440 A US 3051440A US 44179 A US44179 A US 44179A US 4417960 A US4417960 A US 4417960A US 3051440 A US3051440 A US 3051440A
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US
United States
Prior art keywords
rotor
blades
body part
air driven
band
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
US44179A
Inventor
Chandler Robert Walter
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.)
Lucas Support Services Ltd
Original Assignee
Rotax Ltd
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 Rotax Ltd filed Critical Rotax Ltd
Application granted granted Critical
Publication of US3051440A publication Critical patent/US3051440A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses

Definitions

  • This invention relates to air driven turbines more particularly for use on aircraft, and of the kind having a rotor comprising a central body part carrying a plurality of equi-angularly spaced peripheral blades.
  • the object of the present invention is to provide a turbine rotor in a convenient form whereby the breaking away or detachment of a rotor blade will ensure release of the other rotor blades to restore the dynamic balance of the rotor, and cause the body part of the rotor to slow down.
  • the blades are freely located relative to the central body part and are held in position by means of an encircling member which is locally weakened at at least one angular position.
  • the rotor comprises a central body part a which is dynamically balanced and has in its peripheral portion a plurality of equi-angularly spaced recesses or holes for the reception of pairs of dowels or similar projections b on the turbine blades 0, each blade having a pair of the dowels or similar projections secured thereto so as to extend therefrom in parallel relationship with each other into axially slidable engagement with the corresponding recess or holes in the peripheral portion of the central body part.
  • Encircling the blades 0 is an endless band d which serves to retain the dowels or similar projections b of the blades within their locations in the body part a.
  • the arrangement is such that the pairs of dowels or like projections b serve to locate the blades 0 against angular movement relative to the body part, but the sole means restraining the blades from radial disengagement from the body is the encircling band d.
  • the latter is locally weakened, as by holes, at at least one, but preferably as shown three equi-angularly spaced positions 2, and is designed to P 1 cc break under the centrifugal forces due to its own weight and that of the blades c which it retains when the turbine is rotated at a predetermined speed above its normal operating speeds.
  • the band at being broken when the rotor is rotating all the blades will be thrown from the body part by centrifugal forces thus restoring the dynamic balance of the rotor.
  • the rotor will start to slow down since there are no suitably shaped parts on which the air jets can react to impart the rotation.
  • some of the dowels or like parts b extend through their associated blades into holes or recesses on the band as shown at b1 so as to locate the band d against axial movement.
  • a rotor for an air-driven turbine of the kind specified comprising in combination a central body part, a plurality of blades extending in equi-angularly spaced relationship from the periphery of said body part, projections rigid with said blades and extending therefrom into axially slidable engagement with openings in the peripheral portion of said body part, and an endless band which encircles said blades to hold them in position on said body part, and which has at least one weakened portion for enabling said band to be broken by centrifugal forces, due to the weight of said band and blades, in the event of the rotor exceeding its normal maximum speed by a predetermined amount.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Tires In General (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Aug. 28, 1962 w. CHANDLER 43,051,44Q
AIR DRIVEN TURBINES Filed July 20. 1960 United States Patent 3,051,440 AIR DRIVEN TURBINES Robert Walter Chandler, Solihull, England, assignor to Rotax Limited, London, England Filed July 20, 1960, Ser. No. 44,179 Claims priority, application Great Britain July 27, 1959 1 Claim. (Cl. 25377) This invention relates to air driven turbines more particularly for use on aircraft, and of the kind having a rotor comprising a central body part carrying a plurality of equi-angularly spaced peripheral blades.
In the event of a blade of such a turbine rotor becoming detached, or being broken away, the dynamic balance of the rotor is upset with the result that there is a grave risk of the rotor as a whole breaking up if it continues to rotate at high speeds. Such breaking up of the rotor may have very serious consequences, more particularly when the turbine is mounted in an aircraft, and the object of the present invention is to provide a turbine rotor in a convenient form whereby the breaking away or detachment of a rotor blade will ensure release of the other rotor blades to restore the dynamic balance of the rotor, and cause the body part of the rotor to slow down.
According to the invention, in a rotor for an air driven turbine of the kind specified the blades are freely located relative to the central body part and are held in position by means of an encircling member which is locally weakened at at least one angular position.
An example of the invention is illustrated in part-sectional side elevation in the accompanying drawing.
Referring to the drawing, the rotor comprises a central body part a which is dynamically balanced and has in its peripheral portion a plurality of equi-angularly spaced recesses or holes for the reception of pairs of dowels or similar projections b on the turbine blades 0, each blade having a pair of the dowels or similar projections secured thereto so as to extend therefrom in parallel relationship with each other into axially slidable engagement with the corresponding recess or holes in the peripheral portion of the central body part.
Encircling the blades 0 is an endless band d which serves to retain the dowels or similar projections b of the blades within their locations in the body part a. The arrangement is such that the pairs of dowels or like projections b serve to locate the blades 0 against angular movement relative to the body part, but the sole means restraining the blades from radial disengagement from the body is the encircling band d. The latter is locally weakened, as by holes, at at least one, but preferably as shown three equi-angularly spaced positions 2, and is designed to P 1 cc break under the centrifugal forces due to its own weight and that of the blades c which it retains when the turbine is rotated at a predetermined speed above its normal operating speeds. In the event of the band at being broken when the rotor is rotating all the blades will be thrown from the body part by centrifugal forces thus restoring the dynamic balance of the rotor. Moreover, as soon as the blades of the rotor are detached the rotor will start to slow down since there are no suitably shaped parts on which the air jets can react to impart the rotation. Conveniently, some of the dowels or like parts b extend through their associated blades into holes or recesses on the band as shown at b1 so as to locate the band d against axial movement.
It has been found in experiments that the detached blades and/ or broken parts of the band can pass from the turbine exhaust without serious damage such as is likely to occur in the event of the body part of the rotor breaking up.
Having thus described my invention what I claim as new and desire to secure by Letters Patent is:
A rotor for an air-driven turbine of the kind specified, comprising in combination a central body part, a plurality of blades extending in equi-angularly spaced relationship from the periphery of said body part, projections rigid with said blades and extending therefrom into axially slidable engagement with openings in the peripheral portion of said body part, and an endless band which encircles said blades to hold them in position on said body part, and which has at least one weakened portion for enabling said band to be broken by centrifugal forces, due to the weight of said band and blades, in the event of the rotor exceeding its normal maximum speed by a predetermined amount.
References Cited in the file of this patent UNITED STATES PATENTS 1,469,045 MacMurchy Sept. 25, 1923 1,634,897 Davis July 5, 1927 2,310,412 Flanders Feb. 9, 1943 2,349,187 Meyer May 16, 1944 2,942,843 Sampson June 28, 1960 2,965,355 Spaeth Dec. 20, 1960 FOREIGN PATENTS 342,900 Germany Oct. 26, 1921 405,301 Italy Feb. 19, 1942 532,372 Great Britain Ian. 22, 1941 537,455 Great Britain June 23, 1941 837,495 Germany Apr. 28, 1952 1,223,925 France Feb. 1, 1960
US44179A 1959-07-27 1960-07-20 Air driven turbines Expired - Lifetime US3051440A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB25636/59A GB895510A (en) 1959-07-27 1959-07-27 Air driven turbines

Publications (1)

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US3051440A true US3051440A (en) 1962-08-28

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DE (1) DE1120469B (en)
GB (1) GB895510A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3271005A (en) * 1964-03-02 1966-09-06 Sundstrand Corp Mechanical overspeed prevention device
US4507047A (en) * 1983-02-28 1985-03-26 Tech Development Inc. Hoop turbine
US5178517A (en) * 1990-08-27 1993-01-12 Ed Reinhorn Turbine bucket rotor construction
WO2006057602A1 (en) 2004-11-23 2006-06-01 Atlas Copco Tools Ab Axial flow turbine with overspeed preventing device

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4509896A (en) * 1982-03-01 1985-04-09 Tech Development Inc. Turbine rotor

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE342900C (en) * 1920-01-08 1921-10-26 Schneider & Cie Soc Head ring for the blades of steam or gas turbines
US1469045A (en) * 1922-04-18 1923-09-25 Westinghouse Electric & Mfg Co Elastic fluid turbine
US1634897A (en) * 1924-11-11 1927-07-05 Westinghouse Electric & Mfg Co Turbine
GB532372A (en) * 1938-08-27 1941-01-22 British Thomson Houston Co Ltd Improvements in and relating to elastic fluid turbines
GB537455A (en) * 1939-04-15 1941-06-23 Westinghouse Electric Int Co Improvements in or relating to turbine blading
US2310412A (en) * 1941-03-08 1943-02-09 Westinghouse Electric & Mfg Co Vibration dampener
US2349187A (en) * 1941-03-08 1944-05-16 Westinghouse Electric & Mfg Co Vibration dampener
DE837495C (en) * 1950-05-05 1952-04-28 Eisen & Stahlind Ag Vane fastening intended for hydraulic converters with an axially flowed through rotor or guide vane ring
FR1223925A (en) * 1959-05-12 1960-06-21 Gen Electric Speed limitation device for turbines
US2942843A (en) * 1956-06-15 1960-06-28 Westinghouse Electric Corp Blade vibration damping structure
US2965355A (en) * 1956-01-17 1960-12-20 United Aircraft Corp Turbine disc burst inhibitor

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE342900C (en) * 1920-01-08 1921-10-26 Schneider & Cie Soc Head ring for the blades of steam or gas turbines
US1469045A (en) * 1922-04-18 1923-09-25 Westinghouse Electric & Mfg Co Elastic fluid turbine
US1634897A (en) * 1924-11-11 1927-07-05 Westinghouse Electric & Mfg Co Turbine
GB532372A (en) * 1938-08-27 1941-01-22 British Thomson Houston Co Ltd Improvements in and relating to elastic fluid turbines
GB537455A (en) * 1939-04-15 1941-06-23 Westinghouse Electric Int Co Improvements in or relating to turbine blading
US2310412A (en) * 1941-03-08 1943-02-09 Westinghouse Electric & Mfg Co Vibration dampener
US2349187A (en) * 1941-03-08 1944-05-16 Westinghouse Electric & Mfg Co Vibration dampener
DE837495C (en) * 1950-05-05 1952-04-28 Eisen & Stahlind Ag Vane fastening intended for hydraulic converters with an axially flowed through rotor or guide vane ring
US2965355A (en) * 1956-01-17 1960-12-20 United Aircraft Corp Turbine disc burst inhibitor
US2942843A (en) * 1956-06-15 1960-06-28 Westinghouse Electric Corp Blade vibration damping structure
FR1223925A (en) * 1959-05-12 1960-06-21 Gen Electric Speed limitation device for turbines

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3271005A (en) * 1964-03-02 1966-09-06 Sundstrand Corp Mechanical overspeed prevention device
US4507047A (en) * 1983-02-28 1985-03-26 Tech Development Inc. Hoop turbine
US5178517A (en) * 1990-08-27 1993-01-12 Ed Reinhorn Turbine bucket rotor construction
WO2006057602A1 (en) 2004-11-23 2006-06-01 Atlas Copco Tools Ab Axial flow turbine with overspeed preventing device

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Publication number Publication date
GB895510A (en) 1962-05-02
DE1120469B (en) 1961-12-28

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