US3712756A - Centrifugally controlled flow modulating valve - Google Patents

Centrifugally controlled flow modulating valve Download PDF

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Publication number
US3712756A
US3712756A US3712756DA US3712756A US 3712756 A US3712756 A US 3712756A US 3712756D A US3712756D A US 3712756DA US 3712756 A US3712756 A US 3712756A
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United States
Prior art keywords
washer
flow
housing
valve assembly
rotational speed
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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
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English (en)
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I Kalikow
E Sterling
W Anderson
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General Electric Co
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General Electric Co
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Publication of US3712756A publication Critical patent/US3712756A/en
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    • 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0971—Speed responsive valve control
    • Y10T137/108—Centrifugal mass type [exclusive of liquid]
    • Y10T137/1135—Rotating valve and rotating governor

Definitions

  • this invention relates to a centrifugally controlled, flow modulating valve and more particularly to a centrifugally controlled valve for modulating the rate of-flow of cooling fluid to the turbine disc and blades of a gas turbine engine.
  • the power output and thermal efficiency of a gas turbine engine can be increased by increasing the temperature of the combustion gases supplied to the turbine blades. In general, however, any such increase is limited by the maximum permissible operating temperature of the turbine rotor and its blades. It is known to the art to use a portion of the compressor air for cooling the turbine rotor and/or its blades. However, any use of the compressor air for turbine cooling decreases the amount of compressor air available for the combustion chamber of the gas turbine, thereby decreasing the thermal efficiency of the engine. Thermal efficiency could be substantially improved in certain operating regimes if the flow of cooling fluid to the turbine rotor and blades could be scheduled to coincide with increases in engine operating temperatures. In general, increased engine operating temperatures coincide with increased engine rotational speed making centrifugally operated valves an attractive means for scheduling cooling flow to the turbine.
  • a valve assembly is included within a gas turbine engine for modulating the rate of flow of cooling fluid to a turbine as a function of rotational speed.
  • the valve assembly includes a valve housing disposed for rotation with the engine shaft.
  • the walls of the housing define an annular plenum chamber therein, and include an inlet port and an outlet port therethrough.
  • a modified Belleville washer is disposed within the plenum chamber for rotation therewith.
  • the modified Belleville washer has an inner and outer frustoconical surface, together with a plurality of weights disposed on the inner frustoconical surface.
  • Increased engine rotational speed operates to modulate the rate of cooling flow through the housing by forcing the frustoconical surfaces of the washer to move toward a radial direction, after which further increased rotational speed causes the inner and outer frustoconical surfaces to invert themselves into outer and inner frustoconical surfaces respectively.
  • This distortion of the washer changes the degree of obstruction which the washer presents to the rate of flow through the housing.
  • FIG. 1 is a cross-sectional view of a gas turbine engine which includes the valve assembly of this inven- DESCRIPTION OF THE PREFERRED EMBODIMENT
  • a gas turbine engine is shown at 10 as comprising a cylindrical housing 12 having an axial flow compressor 14 journaled within the housing adjacent to its forward end.
  • the compressor 14 receives air through an annular air inlet 16 and delivers compressed air to a combustion chamber 18.
  • air is burned with fuel and the resulting combustion gases are directed by a nozzle or guide vane structure 20 to the rotor blades 22 of a turbine rotor 24 for driving the rotor.
  • a shaft 26 drivably connects the turbine rotor 24 with the compressor 14. From the turbine blades 22, the exhaust gases discharge rearwardly into the surrounding atmosphere through an exhaust nozzle 28 whereby the gas turbine engine is provided with forward propulsive thrust.
  • the gas turbine structure so far described is conventional.
  • cooling flow modulating valve assembly of this invention is shown generally M31 and provides modulation of cooling flow to the turbine rotor '24 and turbine blades 22 as a function of engine rotational speed.
  • the cooling flow modulating valve assembly 31 is shown in substantial detail as including a housing 32 which is either formed integral with, or attached to, a shaft 26 for rotation therewith.
  • Housing 32 defines an annular plenum chamber 34, through which compressor cooling air is directed. Cooling air is directed to the valve housing 32 through an annular conduit 30 which remains in fixed position relative to the rotating housing. Cooling air flow enters the valve housing from conduit 30 through an annular inlet port 40. Sealing between the conduit 30 and valve housing 32 is provided by means of two axially spaced labyrinth seals 70, 72. Cooling air flow exits from the valve housing through an annular conduit 44, whereupon it is directed radially outwardly over the turbine rotor disc 24 and thence through openings 45 into the turbine rotor blades and out through suitable openings in the blades (not shown).
  • the annular plenum chamber 34 includes an inner concentric surface 36 having a circumferential groove 42 in the surface thereof, and two axially spaced, outer concentric surfaces 38, 48 between which the annular inlet port 40 is disposed.
  • the valve assembly 31 also includes a Belleville washer 50, the details of which may be better understood by referring to FIGS. 3d and 3b in conjunction with FIG. 2.
  • the Belleville washer 50 includes opposing inner and outer frustoconical surfaces 52, 54, together with an inner concentric edge 56 and an outer concentric edge 58.
  • the inner frustoconical surface 52 of the Belleville washer is preferably modified by inclusion of a plurality of circumferentially spaced weights 60 thereon, which may be characterized as integral radially extending fins.
  • the inner concentric edge 56 of the modified Belleville washer is preferably radiused for seating engagement within the groove 42.
  • the minimum axial width of the outer concentric edge 58 of the modified Belleville washer is determined by the axial width of the inlet port 40.
  • the outer concentric surface 38 of the plenum chamber 34 is of sufficient radius to clear the outer concentric edge 58 of the modified Belleville washer.
  • the washer is preloaded so as to force the frustoconical surfaces radially outward by abutting engagement of the inner frustoconical surface 52 of the washer with the circumferential edge of the outer concentric surface 48 of the plenum chamber.
  • Pressure on either side of the modified Belleville washer is maintained equal by means of passages or undercuts shown generally at 49 which establish flow communication between both sides of the washer.
  • At least one axially extending drive pin 62 interconnects the wall of the valve housing 32 to the modified Belleville washer 50 to insure rotation of both the housing and washer without circumferential slippage therebetween.
  • the drive pin 62 is free to axially slide within its engaging slot so as not to constrain axial movement of the modified Belleville washer within the housing.
  • the modified Belleville washer occupies the position shown by solid lines in FIG. 2.
  • the outer concentric edge 58 of the modified Belleville washer obstructs compressor cooling air flow through the annular inlet port 40.
  • increased centrifugal force acting on the Belleville washer and its associated weights gradually generates an overturning moment which forces the inner and outer frustoconical surfaces 52, 54 toward substantial radial alignment with the center axis.
  • the modified Belleville washer may be made of a spring steel alloy such as is sold under the trade name of lnconel. Spring steel also provides for return of the washer back to its original configuration upon decreased engine rotational speed.
  • Curve B characterizes a Belleville washer wherein the deflection is a function of the engine RPM.
  • a modulating valve having this washer therefore would allow a gradual increase of compressor cooling air flow to the turbine disc and blades for increased engine rotational speed.
  • Such a valve would include a modified Belleville washer characterized by curve C, wherein the area of steep slope represents an area of rapidly changing washer deflection for small changes in engine rotational speed. It has been found that changing the geometry of the sides of the modified Belleville washer by axially thinning the washer results in the steeper sloped curve C. Also, reducing the thickness of the weights 60 has been found to delay the start of the steep portion of the curve. There may also be engine applications where it becomes desirable to have the modulating valve open at a different engine rotational speed from that which the valve closes. The deflection of such a washer is shown graphically by curve A, wherein the hysteresis is the result of an even further axial thinning of the washer.
  • Preloading the washer in the previously described manner eliminates the slight gradual deflection of the washer at low engine rotational speeds, thereby narrowing the differential speed within which substantially all washer deflection occurs.
  • the variety of curves shown graphically in FIG. 4 are indicative of the increased accuracy and flexibility with which turbine cooling flow may be modulated by the valve of this invention.
  • the modulating valve housing is shown generally at 32' and is either formed integral with or attached to the shaft 26 for rotation therewith. Housing 32' also defines an annular plenum chamber 34' through which compressor cooling air is directed.
  • the annular plenum chamber 34' includes an inner concentric surface 36 having a pair of axially spaced, circumferential grooves 42, 42' in the surface thereof.
  • a pair of axially spaced, annular inlet ports 40, 40' direct cooling air through the outer concentric surface of the plenum chamber.
  • the plenum chamber 34 includes two back to back modified Belleville washers 50, 50' wherein washer 50' may be identical with washer 50.
  • the washers 50, 50' include inner concentric edges 56, 56 radiused for seating engagement with the grooves 42, 42 respectively.
  • the inlet ports 40, 40' are axially divided by an annular rib 80 which is maintained in fixed relation to the valve housing by means of a plurality of circumferentially spaced apart, axial ribs 82.
  • An inner concentric surface 84 of the annular rib 80 is of sufficient radius to clear the outer concentric edges 58, 58 of the modified Belleville washers 50, 50'.
  • the modified Belleville washers occupy the positions shown in solid lines and the outer concentric edges 58, 58' obstruct compressor cooling air flow through the annular inlet ports 40, 40' respectively.
  • increased centrifugal force acting on the modified Belleville washers gradually forces the frustoconical surfaces of the washers to invert themselves in the manner previously described, thereby allowing increased cooling air flow through the plenum chamber and thence to the turbine rotor or blades.
  • the inner frustoconical layer may be of a metal having a higher coefficient of thermal expansion than the outer frustoconical layer, such that an increased temperature causes a nonuniform expansion of the Belleville washer, causing it to actuate at a lower engine rotational speed.
  • a valve assembly for modulating the flow of fluid therethrough as a function of rotational speed comprises:
  • valve housing disposed for rotation about a central axis wherein the walls of the housing define an annular plenum chamber therein and include an inlet port and outlet port therethrough;
  • At least one Belleville washer having an inner and outer frustoconical surface, wherein the washer is disposed within the plenum chamber for rotation therewith, such that increased rotational speed and centrifugal force operate to modulate the rate of fluid flow through the housing by forcing the frustoconical surfaces of the washer to move toward a radial direction, after which continued increased centrifugal force causes the inner and outer frustoconical surfaces to invert themselves into outer and inner frustoconical surfaces respectively, thereby changing the degree of obstruction which the washer presents to the rate of flow through the housing.
  • valve assembly of claim 2 as include in a gas turbine engine wherein the valve modulates cooling flow to a turbine.
  • inlet port is an annular opening through the outer radial wall of the housing and the outer concentric edge of the washer substantially obstructs the flow of fluid through the inlet port such that increased rotational speed and centrifugal force operate to modulate the rate of fluid flow by forcing the outer concentric edge of the washer away from the inlet port.
  • valve assembly of claim 4 wherein the inner concentric edge of the washer is restrained from axial translation upon increased rotational speed and centrifugal force by engagement within an annular groove in the inner concentric surface of the annular plenum and circumferential slippage between the washer and housing is restrained by an axially extending pin, the opposing ends of which engage a weight of the washer and wall of the housing respectively.
  • weights I are radially extending fins which project from the inner frustoconical surface of the washer.
  • valve assembly of claim 2 including a second annular opening axially spaced apart from the first opening and a second modified Belleville washer in back to back relationship with the first washer so that the outer concentric edge of the second washer substantially obstructs the flow of fluid through the second annular opening, wherein increased rotational speed and centrifugal force operate to modulate the rate of fluid flow by moving the outer concentric edges of the washers away from the respective annular inlet openings.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
US3712756D 1971-07-22 1971-07-22 Centrifugally controlled flow modulating valve Expired - Lifetime US3712756A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US16516871A 1971-07-22 1971-07-22

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US3712756D Expired - Lifetime US3712756A (en) 1971-07-22 1971-07-22 Centrifugally controlled flow modulating valve

Country Status (5)

Country Link
US (1) US3712756A (OSRAM)
BE (1) BE780106A (OSRAM)
DE (1) DE2218705A1 (OSRAM)
FR (1) FR2146715A5 (OSRAM)
IT (1) IT950837B (OSRAM)

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3832090A (en) * 1972-12-01 1974-08-27 Avco Corp Air cooling of turbine blades
US3990812A (en) * 1975-03-03 1976-11-09 United Technologies Corporation Radial inflow blade cooling system
US4213738A (en) * 1978-02-21 1980-07-22 General Motors Corporation Cooling air control valve
US4217755A (en) * 1978-12-04 1980-08-19 General Motors Corporation Cooling air control valve
EP0037897A1 (de) * 1980-04-15 1981-10-21 M.A.N. MASCHINENFABRIK AUGSBURG-NÜRNBERG Aktiengesellschaft Einrichtung zur Kühlung des Inneren einer Gasturbine
EP0140818A1 (en) * 1983-11-03 1985-05-08 United Technologies Corporation Active clearance control
EP0141770A1 (en) * 1983-11-03 1985-05-15 United Technologies Corporation Active clearance control
US4541774A (en) * 1980-05-01 1985-09-17 General Electric Company Turbine cooling air deswirler
US4543038A (en) * 1982-03-08 1985-09-24 The Garrett Corporation Sealing apparatus and method and machinery utilizing same
US4807433A (en) * 1983-05-05 1989-02-28 General Electric Company Turbine cooling air modulation
US5022817A (en) * 1989-09-12 1991-06-11 Allied-Signal Inc. Thermostatic control of turbine cooling air
US5575616A (en) * 1994-10-11 1996-11-19 General Electric Company Turbine cooling flow modulation apparatus
US5941687A (en) * 1996-11-12 1999-08-24 Rolls-Royce Plc Gas turbine engine turbine system
US20090085303A1 (en) * 2005-11-14 2009-04-02 Komatsu Ltd. Rotating wheel mechanism of construction machine and drive wheel mechanism of construction machine
WO2010103054A1 (fr) * 2009-03-12 2010-09-16 Snecma Element de rotor avec un passage de fluide et un element d'obturation du passage, turbomachine comportant l'element de rotor
FR2968718A1 (fr) * 2010-12-10 2012-06-15 Snecma Turboreacteur comprenant un circuit de prelevement d'air de refroidissement a variation de debit automatique
US20130302143A1 (en) * 2010-12-14 2013-11-14 Rolls-Royce Deutschland Ltd & Co Kg Cooling device for a jet engine
FR3086700A1 (fr) * 2018-09-28 2020-04-03 Safran Aircraft Engines Circuit de ventilation d’aubes d’un turbomoteur, equipe d’une valve automatique
US10794286B2 (en) 2016-02-16 2020-10-06 General Electric Company Method and system for modulated turbine cooling as a function of engine health
FR3108658A1 (fr) * 2020-03-24 2021-10-01 Safran Aircraft Engines Rotor de turbine comprenant un dispositif de régulation du débit de fluide de refroidissement et turbomachine comprenant un tel rotor
FR3108659A1 (fr) * 2020-03-24 2021-10-01 Safran Aircraft Engines Rotor de turbine comprenant un dispositif de régulation du débit de fluide de refroidissement et turbomachine comprenant un tel rotor
US11293294B2 (en) 2020-05-22 2022-04-05 Raytheon Technologies Corporation Speed-controlled conditioning valve for high pressure compressor
US11512594B2 (en) * 2020-06-05 2022-11-29 General Electric Company System and method for modulating airflow into a bore of a rotor to control blade tip clearance
US20220412273A1 (en) * 2021-06-25 2022-12-29 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2884867B1 (fr) 2005-04-21 2007-08-03 Snecma Moteurs Sa Dispositif de regulation du debit d'air circulant dans un arbre rotatif d'une turbomachine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2478649A (en) * 1945-12-29 1949-08-09 Gen Electric Fluid seal
US2787960A (en) * 1953-07-24 1957-04-09 Gen Electric Sump pump
US2936715A (en) * 1955-11-14 1960-05-17 Thompson Ramo Wooldridge Inc Seal assembly
US3028181A (en) * 1958-12-26 1962-04-03 Thompson Lee Lavere Seals for rotating shafts
US3366068A (en) * 1965-09-13 1968-01-30 Smedegaard As Fluid circulation pump

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2478649A (en) * 1945-12-29 1949-08-09 Gen Electric Fluid seal
US2787960A (en) * 1953-07-24 1957-04-09 Gen Electric Sump pump
US2936715A (en) * 1955-11-14 1960-05-17 Thompson Ramo Wooldridge Inc Seal assembly
US3028181A (en) * 1958-12-26 1962-04-03 Thompson Lee Lavere Seals for rotating shafts
US3366068A (en) * 1965-09-13 1968-01-30 Smedegaard As Fluid circulation pump

Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3832090A (en) * 1972-12-01 1974-08-27 Avco Corp Air cooling of turbine blades
US3990812A (en) * 1975-03-03 1976-11-09 United Technologies Corporation Radial inflow blade cooling system
US4213738A (en) * 1978-02-21 1980-07-22 General Motors Corporation Cooling air control valve
US4217755A (en) * 1978-12-04 1980-08-19 General Motors Corporation Cooling air control valve
EP0037897A1 (de) * 1980-04-15 1981-10-21 M.A.N. MASCHINENFABRIK AUGSBURG-NÜRNBERG Aktiengesellschaft Einrichtung zur Kühlung des Inneren einer Gasturbine
US4541774A (en) * 1980-05-01 1985-09-17 General Electric Company Turbine cooling air deswirler
US4543038A (en) * 1982-03-08 1985-09-24 The Garrett Corporation Sealing apparatus and method and machinery utilizing same
US4807433A (en) * 1983-05-05 1989-02-28 General Electric Company Turbine cooling air modulation
EP0141770A1 (en) * 1983-11-03 1985-05-15 United Technologies Corporation Active clearance control
EP0140818A1 (en) * 1983-11-03 1985-05-08 United Technologies Corporation Active clearance control
US5022817A (en) * 1989-09-12 1991-06-11 Allied-Signal Inc. Thermostatic control of turbine cooling air
US5575616A (en) * 1994-10-11 1996-11-19 General Electric Company Turbine cooling flow modulation apparatus
US5941687A (en) * 1996-11-12 1999-08-24 Rolls-Royce Plc Gas turbine engine turbine system
US8020874B2 (en) * 2005-11-14 2011-09-20 Komatsu Ltd. Rotating wheel mechanism of construction machine and drive wheel mechanism of construction machine
US20090085303A1 (en) * 2005-11-14 2009-04-02 Komatsu Ltd. Rotating wheel mechanism of construction machine and drive wheel mechanism of construction machine
WO2010103054A1 (fr) * 2009-03-12 2010-09-16 Snecma Element de rotor avec un passage de fluide et un element d'obturation du passage, turbomachine comportant l'element de rotor
CN102341568A (zh) * 2009-03-12 2012-02-01 斯奈克玛 具有流体通道和通道阻塞部件的转子元件及包括转子元件的涡轮发动机
FR2943094A1 (fr) * 2009-03-12 2010-09-17 Snecma Element de rotor avec un passage de fluide et un element d'obturation du passage, turbomachine comportant l'element de rotor.
US8882453B2 (en) 2009-03-12 2014-11-11 Snecma Rotor element with a fluid passage and passage-blocking member and turbine engine including the rotor element
US9062605B2 (en) 2010-12-10 2015-06-23 Snecma Turbojet including an automatically variable flow rate bleed circuit for cooling air
FR2968718A1 (fr) * 2010-12-10 2012-06-15 Snecma Turboreacteur comprenant un circuit de prelevement d'air de refroidissement a variation de debit automatique
US9657592B2 (en) * 2010-12-14 2017-05-23 Rolls-Royce Deutschland Ltd & Co Kg Cooling device for a jet engine
US20130302143A1 (en) * 2010-12-14 2013-11-14 Rolls-Royce Deutschland Ltd & Co Kg Cooling device for a jet engine
US10794286B2 (en) 2016-02-16 2020-10-06 General Electric Company Method and system for modulated turbine cooling as a function of engine health
FR3086700A1 (fr) * 2018-09-28 2020-04-03 Safran Aircraft Engines Circuit de ventilation d’aubes d’un turbomoteur, equipe d’une valve automatique
FR3108658A1 (fr) * 2020-03-24 2021-10-01 Safran Aircraft Engines Rotor de turbine comprenant un dispositif de régulation du débit de fluide de refroidissement et turbomachine comprenant un tel rotor
FR3108659A1 (fr) * 2020-03-24 2021-10-01 Safran Aircraft Engines Rotor de turbine comprenant un dispositif de régulation du débit de fluide de refroidissement et turbomachine comprenant un tel rotor
US11293294B2 (en) 2020-05-22 2022-04-05 Raytheon Technologies Corporation Speed-controlled conditioning valve for high pressure compressor
US11512594B2 (en) * 2020-06-05 2022-11-29 General Electric Company System and method for modulating airflow into a bore of a rotor to control blade tip clearance
US20220412273A1 (en) * 2021-06-25 2022-12-29 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine engine
US11674453B2 (en) * 2021-06-25 2023-06-13 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine engine having hollow low-pressure shaft with integrated valve for delivering hot compressed air to a fan disk

Also Published As

Publication number Publication date
BE780106A (fr) 1972-07-03
DE2218705A1 (de) 1973-02-01
FR2146715A5 (OSRAM) 1973-03-02
IT950837B (it) 1973-06-20

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