US2684568A - Apparatus for ascertaining and regulating deformation of the housing and rotor elements of an elastic fluid turbomachine - Google Patents

Apparatus for ascertaining and regulating deformation of the housing and rotor elements of an elastic fluid turbomachine Download PDF

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Publication number
US2684568A
US2684568A US207912A US20791251A US2684568A US 2684568 A US2684568 A US 2684568A US 207912 A US207912 A US 207912A US 20791251 A US20791251 A US 20791251A US 2684568 A US2684568 A US 2684568A
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United States
Prior art keywords
housing
rotor
pressure
tube
deformation
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US207912A
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English (en)
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Senger Ulrich
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
    • G01B5/30—Measuring arrangements characterised by the use of mechanical techniques for measuring the deformation in a solid, e.g. mechanical strain gauge
    • 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
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • 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
    • F01D21/08—Restoring position
    • 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
    • F01D21/12—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to temperature

Definitions

  • the present invention relates to an improved apparatus for ascertaining and regulating deformation of the housing and rotor elements of an elastic fluid turbo-machine caused by unequal heat distribution with a view of maintaining minimum but accurate clearance between stationary and running parts of the machine.
  • the maintenance of the smallest possible radial clearance is of decisive importance for a good efiiciency in all turbines, in particular turbines with relatively small volumes of steam.
  • the smallest possible radial clearance of packings and blades is determined in all turbine models more or less empirically, without it being always possible to avoid with certainty a radial brushing between housing and rotor unless uneconomically large clearances are to be used.
  • the brushing of blades and packings is often caused in that when starting the cold machine, during load variations, and when stopping, rotor and housing do not expand in radial and axial direction (depending on the model) with the same constant, so that enlargements or dangerous reductions of the radial clearances may occur temporarily on the entire periphery.
  • a current of a gaseous fluid which may be a vaporized liquid such as steam or a normally gaseous substance such as air in such a way that deformation of the housing and rotor causes a pressure variation in the gas fluid which can be used to indicate or regulate the deformation.
  • a device for carrying out the method according to the invention is characterized by a measuring tube which is connected in the current of the gaseous fluid and which is installed in the housing of the turbo-machine opposite a revolving surface of the rotor in such a way that one end constituting the mouth is spaced at a small distance from and confronts the revolving surface, its other end bein provided with a throttle orifice whose cross section is approximately of the same size as the mean cross section of the gap between the mouth of the measuring tube confronting the rotor and the revolving surface of the rotor, in such a way that the pressure variation caused in the measuring tube by the deformation of the housing and rotor can be used to indicate or respectively to regulate the deformation.
  • the pressure variation caused in the nieasuring tube by the deformation of the housing and/ or rotor can advantageously be used also to actuate a heating device for the lower part oi the machine housing.
  • the pressure variation caused in the measuring tube by the deformation of the housing may actuate a valve, whereby a gaseous fluid of suitable temperature is conveyed to the interior of the turbo-machine in such a way that the amount thereof regulates the deformation of the housing.
  • a gaseous fluid of suitable temperature whose quantity, automatically influenced by the measuring tube and the housing deformation, regulates the housing deformation, may be conveyed to the interior of the machine through the measuring tube itself.
  • the arrangement may be made in such a way that in the upper as well as in the lower part of the housing a measuring tube for each is installed, which tubes can be used jointly for a diiferential measurement as well as separately for a measurement of the upper and lower blade clearances.
  • Fig. 1 is a view in vertical section of the measuring device as installed on a turbo-machine
  • Fig. 2 is a schematic view which illustrates an application of the measuring device shown in Fig. 1 wherein a gaseous fluid such as fresh steam under pressure or alternatively compressed air are utilized to ascertain and indicate deformation in the machine;
  • a gaseous fluid such as fresh steam under pressure or alternatively compressed air
  • Fig. 3 shows an arrangement similar to Fig. 2 but wherein the pressure measuring device is connected to a stage of lower pressure
  • Fig. 2 illustrates schematically an application of the measuring device to regulation of the our vature of the housing when the turbo-machine is disconnected from its source of not driving gaseous fluid, by controlling its temperature, the medium used for temperature control being a heated gaseous fluid;
  • Fig. 5 shows an embodiment similar to Fig. 4 wherein the heating medium is an electric type heater element
  • Fig. 6 shows another schematic arrangement employing two measuring devices for ascertaining deformation of the machine at diametrally opposite points on the rotor in the upper and lower parts of the housing.
  • a cylindrical measuring tube i having a bore ic of uniform diameter is introduced from the exterior into the housing 2 of a turbomachine, for example between a series of guide blades or in other suitable interstices, so that its lower end or mouth to facing the rotor 3 approaches radially a suitable cylindrical surface of the latter, for example the drum surface or the covering bands of a series of moving blades 4.
  • the tube mouth to confronts the periphery of the rotor and is spaced from the same by a distance of about 0.5 mm. to 1.0 mm.
  • a gaseous fluid such as air or fr sh steam is introduced under constant pressure and flows into the tube through an orifice to in nozzle plate 6, the cross section i of orifice to being preferably substantially equal. to the mean cross section of the gap existing between the tube mouth and the periphery of the rotor 3. That is, area i is equal to the circumference of the bore of the tube mouth to multiplied by the mean distance from the mouth to the rotor surface.
  • the back pressure Q0 ⁇ : in the tube l between the lower end or mouth la and nozzle ii is wholly dependent upon the radial clearance between housing and rotor.
  • pressure 2:; is independent of the stage pressure 232, so that here the accuracy of measurement is especially great and the measurement especially simple.
  • a manometer 9 connected into the pressure chamber portion of tube l intermediate nozzle s and the lower end la measures the pressure :01; in this chamber portion of the tube and since such pressure varies with the distance between tube end is and the face of rotor 3, the scale on the manometer can be calibrated to indicate radial clearance between housing and rotor.
  • the same fres steam as is used for driving the turbine can be conveyed to tube l through valve 1', or alternatively, some other vaporous or gaseous substance for example air under constant pressure can be led into tube 5 through valve 8, the two valves and 3 being of course so arranged in the gas supply lines 75 that steam or air can be admitted to the latter in an alternative manner.
  • tube l in the turbine is the as shown l.
  • Manometer l, or any other like indicating or recording device which may be employed in lieu thereof, will accordingly indicate every variation in pressure in tube 5 and hence every variation in radial clearance between the lower end la of tube l and the surface of rotor
  • Fig. 3 illustrates a slightly different embodiment.
  • Fig. 1 the same fres steam as is used for driving the turbine can be conveyed to tube l through valve 1', or alternatively, some other vaporous or gaseous substance for example air under constant pressure can be led into tube 5 through valve 8, the two valves and 3 being of course so arranged in the gas
  • the gas supply line 5 to tube i contains a branch line 5a, leading to the interior of the upper part 2c of the turbine housing.
  • a valve 32 in the branch line 511 is controlled automatically in accordance with the variation in pressure pl; in tube l over a pressure responsive regulator i i to convey into the upper housing part is when the machine is so disconnected, more or less of a gaseous heating medium such as steam at a suitable temperature which functions to influence the temperature distribution inside of the housing.
  • Fig. 5 shows still another arrangement for regulating the state of curvature of the turbine housing with the turbine disconnected from its source of driving fluid and the shaft rotating device running.
  • an electrical heating unit I5 associated in heat transverse relation with the lower part 22; of the turbine housing is controlled by a regulator 13 responsive in accordance with the change in pressure he within the pressure chamber of measuring tube Regulator i3 actuates a switch 14 connected in the electric power supply line to heater I5 and the arrangement is such that heater i5 is connected whenever the measured pressure X exceeds a preselected value and is disconnected whenever pressure e falls below such value.
  • the pressure fluid used in measurement of the pressure enters tube 1 through supply line 5 as before.
  • measuring units l and i may be used independently, as shown, with the read ings being taken on manometers 9 and 9, respectively or may be utilized together in such mannor that the resultant regulatory action is made dependent upon the pressure diiferential between the two units.
  • the invention is most suitable as a solution for one of the most diflicult problems encountered in operation of the most modern of high-pressure, preconnected steam turbine plants, namely that of keeping the turbines in readiness for immediate restarting after having been shut down, during a period of reduced load or for any other reason.
  • a turbo-machine of apparatus for measuring and regulating deformation of the housing and rotor elements of said turbo-machine caused by unequal heat distribution, said apparatus comprising a tube secured to said housing and extending therefrom in the direction of the rotor surface with the mouth of said tube disposed closely to and confronting the rotor surface, a throttling orifice disposed in said tube to establish a pressure chamber therein between said orifice and tube mouth, a valve controlled inlet on said housing for admitting hot gaseous driving fluid to the interior thereof for driving said rotor during normal operation of said turbo-machine when delivering power, an auxiliary motor coupled to said rotor for rotating the latter when the hot driving fluid is cut on at said inlet, means for admitting a portion of said hot driving fluid into the pressure chamber in said tube for flow through the tube mouth against the surface of said rotor, the fluid pressure variation in said chamber being propor-- tional to the variation in distance between the tube mouth and rotor surface, means for heating said housing, and
  • Apparatus for measuring and regulating deformation of a turbo-machine as defined in claim 1 wherein the means for heating said housing is comprised of a valve controlled auxiliary inlet to the interior of said housing at the upper portion thereof through which heated gaseous fluid is passed to the upper interior portion of the housing, and operation of the valve controlling said auxiliary inlet is regulated by the pressure variations in said chamber.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
US207912A 1950-02-04 1951-01-26 Apparatus for ascertaining and regulating deformation of the housing and rotor elements of an elastic fluid turbomachine Expired - Lifetime US2684568A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH698898X 1950-02-04

Publications (1)

Publication Number Publication Date
US2684568A true US2684568A (en) 1954-07-27

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US207912A Expired - Lifetime US2684568A (en) 1950-02-04 1951-01-26 Apparatus for ascertaining and regulating deformation of the housing and rotor elements of an elastic fluid turbomachine

Country Status (7)

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US (1) US2684568A (d)
BE (1) BE500887A (d)
CH (1) CH280276A (d)
DE (1) DE821634C (d)
FR (1) FR1031829A (d)
GB (1) GB698898A (d)
NL (1) NL80814C (d)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3176502A (en) * 1963-07-26 1965-04-06 Pratt & Whitney Inc Pneumatic gage
US3220244A (en) * 1963-09-06 1965-11-30 Cooper Bessemer Corp Thrust bearing wear sensing device
US3754433A (en) * 1971-09-17 1973-08-28 Bendix Corp Fluidic proximity sensor
US4343592A (en) * 1979-06-06 1982-08-10 Rolls-Royce Limited Static shroud for a rotor
US4419044A (en) * 1980-12-18 1983-12-06 Rolls-Royce Limited Gas turbine engine
US4482293A (en) * 1981-03-20 1984-11-13 Rolls-Royce Limited Casing support for a gas turbine engine
US4523451A (en) * 1983-11-17 1985-06-18 Borg-Warner Corporation Hydraulic proximity probe
US4632635A (en) * 1984-12-24 1986-12-30 Allied Corporation Turbine blade clearance controller
US4733529A (en) * 1986-09-26 1988-03-29 Cef Industries, Inc. Performance envelope extension device for a gas turbine engine
US4845991A (en) * 1986-12-22 1989-07-11 Combustion Engineering, Inc. Hydraulic clearance measurement system
US6657217B2 (en) 2001-04-10 2003-12-02 York International Corporation Probe for sensing movement in a compressor system
US20050005679A1 (en) * 2003-03-28 2005-01-13 Herbert Dingfelder Device and method for measuring mechanical path lengths by means of pneumatic pressure, in particular for sliding carbon contacts
EP1505262A1 (de) * 2003-08-08 2005-02-09 Siemens Aktiengesellschaft Verfahren und Vorrichtung zur Messung der Breite eines Radialspaltes
US20060159547A1 (en) * 2005-01-15 2006-07-20 Siemens Westinghouse Power Corporation Warning system for turbine component contact
US20130125552A1 (en) * 2011-11-23 2013-05-23 General Electric Company Gas turbine engine lockout reduction
US10947993B2 (en) 2017-11-27 2021-03-16 General Electric Company Thermal gradient attenuation structure to mitigate rotor bow in turbine engine
CN112780367A (zh) * 2021-03-10 2021-05-11 浙江浙能技术研究院有限公司 一种汽轮机坐缸式轴承及轴承座微小形变在线监测方法及装置
US11879411B2 (en) 2022-04-07 2024-01-23 General Electric Company System and method for mitigating bowed rotor in a gas turbine engine

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2994472A (en) * 1958-12-29 1961-08-01 Gen Electric Tip clearance control system for turbomachines
US3039737A (en) * 1959-04-13 1962-06-19 Int Harvester Co Device for controlling clearance between rotor and shroud of a turbine
DE1160652B (de) * 1960-06-01 1964-01-02 Maschf Augsburg Nuernberg Ag Einrichtung zum Messen der gegenseitigen axialen Verschiebung zweier Turbinenteile
CS193219B1 (en) * 1977-04-16 1979-10-31 Jan Jicha Connection for continuous measuring of the clearance,gaps and shifts
GB2153911A (en) * 1984-02-10 1985-08-29 Hobourn Eaton Ltd Method of checking radial clearances in rotary machines

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB202691A (en) * 1922-04-27 1923-08-27 Henry Lewis Guy Improvements in devices for indicating or measuring distances or movements of machine parts or other solid bodies
US1927750A (en) * 1929-05-21 1933-09-19 Materiel Automobile S A C M A Measuring instrument controls for machines
US1971271A (en) * 1930-09-09 1934-08-21 Material Automobile S A C M A Pneumatic measuring device
US2357569A (en) * 1942-06-17 1944-09-05 Gen Motors Corp Gauge
US2523564A (en) * 1942-12-04 1950-09-26 Estavex S A Pneumatic measuring apparatus

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB202691A (en) * 1922-04-27 1923-08-27 Henry Lewis Guy Improvements in devices for indicating or measuring distances or movements of machine parts or other solid bodies
US1927750A (en) * 1929-05-21 1933-09-19 Materiel Automobile S A C M A Measuring instrument controls for machines
US1971271A (en) * 1930-09-09 1934-08-21 Material Automobile S A C M A Pneumatic measuring device
US2357569A (en) * 1942-06-17 1944-09-05 Gen Motors Corp Gauge
US2523564A (en) * 1942-12-04 1950-09-26 Estavex S A Pneumatic measuring apparatus

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3176502A (en) * 1963-07-26 1965-04-06 Pratt & Whitney Inc Pneumatic gage
US3220244A (en) * 1963-09-06 1965-11-30 Cooper Bessemer Corp Thrust bearing wear sensing device
US3754433A (en) * 1971-09-17 1973-08-28 Bendix Corp Fluidic proximity sensor
US4343592A (en) * 1979-06-06 1982-08-10 Rolls-Royce Limited Static shroud for a rotor
US4419044A (en) * 1980-12-18 1983-12-06 Rolls-Royce Limited Gas turbine engine
US4482293A (en) * 1981-03-20 1984-11-13 Rolls-Royce Limited Casing support for a gas turbine engine
US4523451A (en) * 1983-11-17 1985-06-18 Borg-Warner Corporation Hydraulic proximity probe
US4632635A (en) * 1984-12-24 1986-12-30 Allied Corporation Turbine blade clearance controller
US4733529A (en) * 1986-09-26 1988-03-29 Cef Industries, Inc. Performance envelope extension device for a gas turbine engine
US4845991A (en) * 1986-12-22 1989-07-11 Combustion Engineering, Inc. Hydraulic clearance measurement system
US6657217B2 (en) 2001-04-10 2003-12-02 York International Corporation Probe for sensing movement in a compressor system
US6744061B2 (en) 2001-04-10 2004-06-01 York International Corporation System and method for sensing movement in a compressor system
US20050005679A1 (en) * 2003-03-28 2005-01-13 Herbert Dingfelder Device and method for measuring mechanical path lengths by means of pneumatic pressure, in particular for sliding carbon contacts
US7010959B2 (en) * 2003-03-28 2006-03-14 Schleifring Und Apparatebau Gmbh Device and method for measuring mechanical path lengths by means of pneumatic pressure, in particular for sliding carbon contacts
EP1505262A1 (de) * 2003-08-08 2005-02-09 Siemens Aktiengesellschaft Verfahren und Vorrichtung zur Messung der Breite eines Radialspaltes
US20060159547A1 (en) * 2005-01-15 2006-07-20 Siemens Westinghouse Power Corporation Warning system for turbine component contact
US7207768B2 (en) 2005-01-15 2007-04-24 Siemens Power Generation, Inc. Warning system for turbine component contact
US20130125552A1 (en) * 2011-11-23 2013-05-23 General Electric Company Gas turbine engine lockout reduction
CN103133145A (zh) * 2011-11-23 2013-06-05 通用电气公司 燃气涡轮发动机停工的减少
US8776530B2 (en) * 2011-11-23 2014-07-15 General Electric Company Gas turbine engine lockout reduction
CN103133145B (zh) * 2011-11-23 2016-08-31 通用电气公司 减少燃气涡轮发动机的停工时间的方法
EP2597274A3 (en) * 2011-11-23 2017-06-07 General Electric Company Gas turbine engine lockout-time reduction
US10947993B2 (en) 2017-11-27 2021-03-16 General Electric Company Thermal gradient attenuation structure to mitigate rotor bow in turbine engine
CN112780367A (zh) * 2021-03-10 2021-05-11 浙江浙能技术研究院有限公司 一种汽轮机坐缸式轴承及轴承座微小形变在线监测方法及装置
US11879411B2 (en) 2022-04-07 2024-01-23 General Electric Company System and method for mitigating bowed rotor in a gas turbine engine

Also Published As

Publication number Publication date
DE821634C (de) 1951-11-19
BE500887A (d)
GB698898A (en) 1953-10-28
CH280276A (de) 1952-01-15
NL80814C (d)
FR1031829A (fr) 1953-06-26

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