US3825367A - Reversible turbine with inlet and brake control system - Google Patents

Reversible turbine with inlet and brake control system Download PDF

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Publication number
US3825367A
US3825367A US00323236A US32323673A US3825367A US 3825367 A US3825367 A US 3825367A US 00323236 A US00323236 A US 00323236A US 32323673 A US32323673 A US 32323673A US 3825367 A US3825367 A US 3825367A
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US
United States
Prior art keywords
turbine
valve
shaft
blade
discs
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
US00323236A
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English (en)
Inventor
G Lewis
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.)
Northrop Grumman Properties Ltd
Original Assignee
Lucas Aerospace Ltd
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Filing date
Publication date
Application filed by Lucas Aerospace Ltd filed Critical Lucas Aerospace Ltd
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Publication of US3825367A publication Critical patent/US3825367A/en
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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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/30—Non-positive-displacement machines or engines, e.g. steam turbines characterised by having a single rotor operable in either direction of rotation, e.g. by reversing of blades
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts

Definitions

  • a turbine includes a rotor having two sets of blades, gas flow through one blade set urging the rotor in the opposite direction to gas flow through the other blade set.
  • a valve between the rotor and the turbine inlet enables gas flow to the blade sets to be selectively controlled, an increased flow to one of the sets being preceded by a decreased flow to the other set.
  • SHEET EDF 6 REVERSIBLE TURBINE WITH INLET AND BRAKE CONTROL SYSTEM This invention relates to reversible turbine, and has an object to provide such a turbine in a convenient form.
  • a turbine comprises a housing, a fluid inlet in the housing, a shaft rotatable in the housing, first and second turbine rotor blade arrangements drivingly connected to said shaft, a fluid flow to said first and second blade arrangements respectively acting to rotate said shaft in opposite directions, and a valve for controlling fluid flow from said inlet to said rotors, said valve being arranged so that an increase in fluid flow to a selected one of said blade arrangements is preceded by a decrease in the flow to the other blade arrangement.
  • FIG. 1 is a section through a gas turbine
  • FIGS. 2 to 3 are sections on the corresponding lines in FIG. 1,
  • FIG. 4 is a view on arrow 4 in FIG. 1,
  • FIG. 5 is a section through an alternative form of turbine
  • FIG. 6 is a pictorial view of a detail of FIG. 5.
  • a body 10 has an inlet 11 which is, in use, supplied with a gas under pressure.
  • Journalled in the body 10 is a shaft 12 to which a rotor 13 is secured by splines 14 and a bolt 15.
  • Rotor 13 has an arrangement of axial flow turbine blades 16 and also an arrangement of radial flow blades 17.
  • Associated with the blades 16,17 respectively are stator vanes 18, 19. The arrangement is such that a gas flow through vanes 18 and blades 16 rotates rotor 13 in the opposite direction to a flow through vanes 19 and blades 17.
  • An outer annular passage 20 communicates with vanes 18 and a concentric inner annular passage 21 communicates with vanes 19.
  • Surrounding portion 24 is a sleeve 25 having slotted ports 26.
  • Sleeve 25 is rotatable on portion 24 and co-operates with ports 22, 23 to provide a valve between the respective passages 20, 21 and inlet 11.
  • the ports 22 are angularly spaced from ports 23 so that sleeve 25 shuts off ports 22 before opening ports 23, and vice versa.
  • Sleeve 25 is rotatable, via gears 27, by an electric motor 28.
  • Motor 28 is controlled by a circuit 29 which is responsive to an input control signal and to a signal from a position transducer 30 coupled to sleeve 25 by a link 31.
  • a stop 32 slidable in a slot 33 in one of the gears 27 limits rotation of sleeve 25.
  • a butterfly valve arrangement 34 which comprises a disc 35 movable to open inlet 11 by a piston 36. Piston 36 is biased in a direction to shut valve 34 by a spring 37. Piston 36 is movable against spring 37 by gas pressure controlled by a valve 38 operated by a solenoid 40. Valve 38 is a two-way valve movable between a position in which piston 36 is subjected, via a passage 39, to the pressure in inlet 11, and a position in which passage 39 is shut off and piston 36 is subjected to atmospheric pressure. Energisation of solenoid 40 thus opens butterfly valve 34, provided there is a sufficient pressure within inlet 11.
  • an output shaft 41 axially aligned with shaft 12.
  • Splined on to shaft 41 is an internal ring gear 42 which forms part of a reduction gear train 43 driven by shaft 12.
  • Shaft 41 also carries a pair of brake discs 44, 45 whose outer faces are respectively engageable by friction discs 46, 47 secured to the body 10.
  • Discs 44, 45 are mounted for axial movement relative to each other and to shaft 41.
  • the inner faces of discs 44, 45 are respectively engageable by friction discs 48, 49 which are both rotatable and axially movable relative to discs 46, 47.
  • Adjacent faces of discs 48, 49 have aligned tapered recesses 50 in which are located balls 51, so that relative rotation of discs 48, 49 urges them apart, brake discs 44, 45 thus being frictionally engaged by the discs on either side.
  • Discs 48, 49 are relatively rotatable by a linkage 52 operable by a piston 53.
  • Piston 53 is responsive to a gas pressure in a passage 54 which communicates with inlet 11 downstream of valve 34. Pressure in passage 54 is applied to piston 53 under control of a two-way valve 55 similar to the valve 38 and operated by a solenoid 56.
  • solenoid 56 is energised piston 53 moves against a spring 57 to the position shown in FIG. 3 to align recesses 50 and therefore release the brake. If solenoid 56 is de-energised, or in the absence of a pressure in passage 54, the brake is applied to arrest shaft 41.
  • shaft 41 In use, with a pressure applied to inlet 11 and with solenoids 40, 56 energised, shaft 41 will be rotated in a direction dependent on the position of sleeve 25. Shaft 41 is thus readily reversible, gas flow to selected one of the turbine blade arrangements 16, 17 being progressively reduced, and finally shut off, before sleeve 25 permits a progressively increasing flow to the other of the blade arrangements.
  • rotor 13 has two arrangements 60, 61 of axial flow turbine blades, arrangement 61 surrounding arrangement 60, as shown pictorially in FIG. 6.
  • stator vanes 62, 63 Associated with the respective blade arrangements 60, 61 are stator vanes 62, 63.
  • a gas flow through vanes 62 and blades turns rotor 13 in the opposite direction to a flow through vanes 63 and blades 61.
  • Operation of sleeve 25 thus enables the direction of rotation and power output to shaft 12 to be varied, as before.
  • a turbine comprising a housing, a fluid inlet in the housing, a shaft rotatable in the housing, a braking arrangement operable to arrest rotation of said shaft, first biasing means .urging said braking arrangement to arrest said shaft, a first piston movable against said first biasing means to cause said braking arrangement to release said shaft, first and second turbine rotor blade arrangements drivingly connected to said shaft, said first and second blade arrangement being respectively responsive to a fluid flow from said inlet to rotate said shaft in opposite directions, a first valve means for providing a decrease in fluid flow from said inlet to one of said blade arrangements prior to providing an increase in fluid flow to the other blade arrangement second valve means between said inlet and said first valve means, second biasing means urging said secondvalve means towards a shut position, a second piston movable against said second biasing means to open said second valve means, a first control valve movable between a first position in which the pressure in said inlet is applied to said second piston and a second position in which said second piston is subjected to atmospheric pressure
  • a turbine as claimed in claim 1 which includes a first annular passage between said first blade arrangement and said valve, and a second annular passage between said second blade arrangement and said valve, one of said annular passages surrounding the other of said annular passages.
  • a turbine as claimed in claim 1 which includes first and second ports in a part of said body, through which ports fluid can flow to aid first and second blade arrangements respectively, and in which said valve includes a closure member movable to selectively uncover said ports.
  • a turbine as claimed in claim 5 in which said do sure member comprises a ported sleeve surrounding said body part.
  • a turbine as claimed in claim 6 in which said sleeve is rotatable relative to said body part.
  • a turbine as claimed in claim 7 which includes a gear train meshing with said sleeve, and an actuator for driving said gear train.
  • a turbine as claimed in claim 7 which includes means for limiting relative rotation between said sleeve and said body part.
  • a turbine as claimed in claim 8 in which said actuator comprises an electric motor and which includes means for providing a first electrical signal dependent on the relative angular positions of said sleeve and said bodypart.
  • a turbine as claimed in claim 10 which includes an electrical control circuit responsive to said first electrical signal and to an input control signal to provide an output signal to said motor.
  • a turbine asclaimed in claim 1 which includes a spring urging said control valve to said second position thereof.
  • a turbine as claimed in claim 12 which includes an electro-magnetic actuator energisable to move said control valve against said spring to its first position.
  • a turbine as claimed in claim 1 which includes a spring biasssing said further control valve to said second position thereof.
  • a turbine as claimed in claim 14 which includes a further electro-magnetic actuator energisable to move said further control valve against its spring to its first position.
  • A'turbine a claimed in claim 16 which includes a second disc on said shaft, axially spaced from said first disc a further friction ring on said body, said further ring being located on a side of said second disc remote from said first disc, and means for biassing said first and second discs apart and into frictional engagement with said ring and said further ring respectively.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Braking Arrangements (AREA)
US00323236A 1972-01-12 1973-01-12 Reversible turbine with inlet and brake control system Expired - Lifetime US3825367A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB140472A GB1411091A (en) 1972-01-12 1972-01-12 Reversible turbine

Publications (1)

Publication Number Publication Date
US3825367A true US3825367A (en) 1974-07-23

Family

ID=9721423

Family Applications (1)

Application Number Title Priority Date Filing Date
US00323236A Expired - Lifetime US3825367A (en) 1972-01-12 1973-01-12 Reversible turbine with inlet and brake control system

Country Status (6)

Country Link
US (1) US3825367A (de)
JP (1) JPS4880908A (de)
DE (1) DE2301254A1 (de)
FR (1) FR2168033B1 (de)
GB (1) GB1411091A (de)
IT (1) IT976787B (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5570244A (en) * 1978-11-20 1980-05-27 Yoshida Seisakusho Kk Dental airrmotor that can be reversed
US4223770A (en) * 1977-11-29 1980-09-23 Messerschmitt-Bolkow-Blohm Gmbh Shaft drive alternately for both directions of rotation
US4245467A (en) * 1978-12-28 1981-01-20 Shank Jr Samuel R Isolated reverse turbine system for gas turbine engines

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU526982B2 (en) * 1981-04-16 1983-02-10 Ransburg Corp. Coating material atomizing and dispensing system
ATE76193T1 (de) * 1988-01-11 1992-05-15 Voest Alpine Ind Anlagen Vorrichtung zur kontinuierlichen entnahme heisser gasproben aus einem reaktionsgefaess.

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR642938A (fr) * 1926-10-25 1928-09-06 Train de renvoi de mouvement par liquide
FR1572493A (de) * 1968-05-09 1969-06-27

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4223770A (en) * 1977-11-29 1980-09-23 Messerschmitt-Bolkow-Blohm Gmbh Shaft drive alternately for both directions of rotation
JPS5570244A (en) * 1978-11-20 1980-05-27 Yoshida Seisakusho Kk Dental airrmotor that can be reversed
US4245467A (en) * 1978-12-28 1981-01-20 Shank Jr Samuel R Isolated reverse turbine system for gas turbine engines

Also Published As

Publication number Publication date
IT976787B (it) 1974-09-10
JPS4880908A (de) 1973-10-30
DE2301254A1 (de) 1973-07-26
GB1411091A (en) 1975-10-22
FR2168033A1 (de) 1973-08-24
FR2168033B1 (de) 1976-05-14

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