US2677273A - Turbine, compressor, or like rotary machine having a pivoted indicator blade responsive to operating conditions - Google Patents

Turbine, compressor, or like rotary machine having a pivoted indicator blade responsive to operating conditions Download PDF

Info

Publication number
US2677273A
US2677273A US67406A US6740648A US2677273A US 2677273 A US2677273 A US 2677273A US 67406 A US67406 A US 67406A US 6740648 A US6740648 A US 6740648A US 2677273 A US2677273 A US 2677273A
Authority
US
United States
Prior art keywords
blade
turbine
compressor
operating conditions
rotary machine
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
US67406A
Other languages
English (en)
Inventor
Johnson William Evelyn Patrick
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development 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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Application granted granted Critical
Publication of US2677273A publication Critical patent/US2677273A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure
    • 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
    • F01D17/02—Arrangement of sensing elements
    • 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
    • F01D17/02—Arrangement of sensing elements
    • F01D17/04—Arrangement of sensing elements responsive to load
    • 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
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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

Definitions

  • This invention relates to bladed rotary fluid.- flow machines, such as turbines or compressors, and is primarily concerned with machines in which the fluid-flow is in the axial direction.
  • One object of the invention is to afford means adapted to respond toan operating condition of the machine, and either to give an indication of variations in such operating condition, or to influence the operation of control means in accordance with such variations.
  • a bladed rotary fluid-flow machine such as a compressor or turbine comprising a stationary structure, in part defining a fluid flow passage through the machine, a row of stator blades supported by the said structure and disposed across the passage, a pivot mounting for at least one of the said stator blades, the axis of pivoting extending in the general direction of the machine axis, further mounting means forsecurely holding the remaining blades, an extension of the said movable blade beyond the confine of the passage, and an element abutting the said extension and resiliently opposing movement of the said extension, which element is operable to initiate an external indication of the extent of the said movement, whereby a reading proportional to the fluid forces acting. on the movable blade is obtainable.
  • the invention may be used to indicate the torque of a turbine (or compressor) and therefore the power delivered or absorbed by integra tion with R. P. M.
  • Figure 1 is a fragmentary transverse section through an axial flow turbine according to a first embodiment.
  • Figure 2 is a section on the line II-II in Figure 1.
  • Figure 3 is a similar view to Figure 1, but showing the second embodiment.
  • Figure 4 is a section on the line IV-IV of Figure 3.
  • the casing I of an axial flow turbine carries stator blades, of which only one row is shown. of that row one blade 2 is pivotally mounted on an axis parallel to that of the turbine, while the remaining blades 3 are fixed.
  • That part of the turbine casing adjacent the row of stator blades shown comprises a pair of annuli 4, 5, secured in abutting relationship to 6 Claims. Cl. 73-133) each other, and to the remainder of the casing'I,
  • the blade 2 is provided with an outward lever arm extension I0 connected to a suitably-supported piezo-electric pressure element I I forming part of an electrical circuit indil0 cated generally by I2 and which includes an electrical indicating device I3 of any suitable known type.
  • a chamber I4 is provided enclosing the lever arm I0 and associated parts.
  • the .pivot' of the blade it is desirable for the .pivot' of the blade to be; so constructed that the internal surface of the fluid passage of the machine is as uninterrupted as is possible, and leakage offluid at'the actual" pivot is reduced to a minimum.
  • the" pivot may, if preferred, be formed by arcuate surfaces at the blade root and complementary surfaces in the casing, as in the construction hereinafter described with reference to Figures 3 and 4.
  • the measuring blades may be commonly connected to one indicator.
  • pivotally movable stator blade I5 is secured in the abutting annuli I9, 20 which constitute part of the stator casing and are held together and to the remaining part of the stator casing by axial bolts (not shown).
  • Arcuate surfaces I6 on the root portion of the blade I5 cooperate with corresponding arcuate surfaces formed in the recesses II, I8 provided in the annuli I9, 20.
  • the blade I5 has a lever arm extension l0 which, as in the previous example, is connected to a suitably supported piezo-electric element II forming part of an electric circuit indicated generally by I2 and including an electric indieating device l3, As in the previous example the lever. armfilflxis housed in. a chamber H so as to sealany working fluid which may have leaked between the cooperating surfaces at the blade root.
  • a bladed. roan-y fluid flow machine as: claimed in claim 1" and: comprising arcuate sur-- faces-a1; the root of said pivotable blade and complementary surfaces,- to-said arcuate surfaces formed in said casing so as to cooperate togethertoform said pivot-mounting.
  • a bladed rotary fluid flow machine asclaimed in claim 1 in which said-stationary casing comprisestwoabutting annuli and complementary recesses in the abutting iaces' ofsaid annuli together forming. an apertu're through the casing, and in which the pivot mounting for said pivotableblad'e comprises a needle bearing within the blade-and-a pin passing through said bearing and "extending across said aperture.
  • Aibladedrntary fluid flowumachine such as a compressor or turbine comprising a stationary casing, in .part' defining an axially-extending fluid flowpassage through themachine, a row-of stator blades mounted inside said casing and disposed across said passage, a pivot mounting for at least one oi said stator blades, the axis of pivoting extending'in the general direction of the machineaxis, mounting means for securely holding theremaining blades of the said row, a chamber external to the casing and positioned in alignment with the saidpivotable blade, a lever arm on said pivotalaleblade extending beyond said pivot mounting into said chamber, a piezoelectric crystal element supported Within the chamber and abutting said lever arm so as to prevent more than limited movement of said leverarm and an electric circuit connected to said element for transmission of signals therefrom-which are proportional to the deformation of the element by lever arm movement, whereby signals proportional itofluidforces acting on said pivotable blade are.
  • A'bladed rotaryfiuid'flow machine such as a compressor or turbine comprising a stationary the passage, a pivot mounting for at least one of the said stator blades, the axis of pivoting extending in the general direction of the ma-- chine-axis, further mounting means for securely holding the remaining blades, an extension of the said movable blade beyond the confine of' the passage, and an elementabuttingthe said extension andresilientlyopposing movement of the-said extension, which element is operable toinitiate an externalindica-tion of, the extent of the. said movement, whereby a. reading proportional to the fluid forces :acting on the 'movable blade is obtainable.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
US67406A 1948-01-07 1948-12-27 Turbine, compressor, or like rotary machine having a pivoted indicator blade responsive to operating conditions Expired - Lifetime US2677273A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB496/48A GB641998A (en) 1948-01-07 1948-01-07 Improvements relating to turbines, compressors, or like rotary machines

Publications (1)

Publication Number Publication Date
US2677273A true US2677273A (en) 1954-05-04

Family

ID=9705364

Family Applications (1)

Application Number Title Priority Date Filing Date
US67406A Expired - Lifetime US2677273A (en) 1948-01-07 1948-12-27 Turbine, compressor, or like rotary machine having a pivoted indicator blade responsive to operating conditions

Country Status (4)

Country Link
US (1) US2677273A (en(2012))
BE (1) BE486585A (en(2012))
FR (1) FR978207A (en(2012))
GB (1) GB641998A (en(2012))

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2841325A (en) * 1954-05-04 1958-07-01 Snecma Axial compressors
US3100622A (en) * 1959-04-07 1963-08-13 Onsrud Machine Works Inc Turbine governor
US3112913A (en) * 1959-04-03 1963-12-03 United Aircraft Corp Turbine speed sensing device
US3396942A (en) * 1967-08-29 1968-08-13 Bristol Siddeley Engines Ltd Rotary bladed machines
US3467358A (en) * 1968-01-08 1969-09-16 Igor Evgenievich Zablotsky Vibrator indicator for turboengine rotor blading
US3514212A (en) * 1968-06-11 1970-05-26 Us Air Force Incipient stall sensor
US3677000A (en) * 1970-04-27 1972-07-18 Faulkner C Thomson System for the detection and control of compressor stall
US4067661A (en) * 1976-10-01 1978-01-10 Caterpillar Tractor Co. Thermally compensated variable turbine nozzle position indicator
US4153388A (en) * 1976-04-30 1979-05-08 Sulzer Brothers Limited Method and apparatus for monitoring the state of oscillation of the blades of a rotor
US10100663B2 (en) 2015-06-04 2018-10-16 Rolls-Royce Plc Actuation arrangement

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3614253A (en) * 1969-05-29 1971-10-19 Robert M Gaertner Engine stall anticipation and reaction device

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1401668A (en) * 1920-01-26 1921-12-27 Bbc Brown Boveri & Cie Method and apparatus for regulating centrifugal compressors
US2014684A (en) * 1932-06-15 1935-09-17 Firm Junkers Motorenbau G M B Apparatus for measuring the performance of engines
US2311684A (en) * 1940-08-23 1943-02-23 Gen Electric Dynamometer type electric machine
US2378958A (en) * 1942-12-11 1945-06-26 Del Conveyor & Mfg Company Propeller construction
US2388208A (en) * 1943-05-27 1945-10-30 B F Sturtevant Co Control vanes for fans
US2409837A (en) * 1944-04-21 1946-10-22 Gen Electric Centrifugal type compressor
US2460778A (en) * 1946-04-12 1949-02-01 United Aircraft Corp Torque regulating device for compressors
US2473382A (en) * 1947-12-24 1949-06-14 Du Pont Apparatus for treating motionpicture film
US2477954A (en) * 1947-04-01 1949-08-02 Blanc Jacques Jean Louis Gas turbine

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1401668A (en) * 1920-01-26 1921-12-27 Bbc Brown Boveri & Cie Method and apparatus for regulating centrifugal compressors
US2014684A (en) * 1932-06-15 1935-09-17 Firm Junkers Motorenbau G M B Apparatus for measuring the performance of engines
US2311684A (en) * 1940-08-23 1943-02-23 Gen Electric Dynamometer type electric machine
US2378958A (en) * 1942-12-11 1945-06-26 Del Conveyor & Mfg Company Propeller construction
US2388208A (en) * 1943-05-27 1945-10-30 B F Sturtevant Co Control vanes for fans
US2409837A (en) * 1944-04-21 1946-10-22 Gen Electric Centrifugal type compressor
US2460778A (en) * 1946-04-12 1949-02-01 United Aircraft Corp Torque regulating device for compressors
US2477954A (en) * 1947-04-01 1949-08-02 Blanc Jacques Jean Louis Gas turbine
US2473382A (en) * 1947-12-24 1949-06-14 Du Pont Apparatus for treating motionpicture film

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2841325A (en) * 1954-05-04 1958-07-01 Snecma Axial compressors
US3112913A (en) * 1959-04-03 1963-12-03 United Aircraft Corp Turbine speed sensing device
US3100622A (en) * 1959-04-07 1963-08-13 Onsrud Machine Works Inc Turbine governor
US3396942A (en) * 1967-08-29 1968-08-13 Bristol Siddeley Engines Ltd Rotary bladed machines
US3467358A (en) * 1968-01-08 1969-09-16 Igor Evgenievich Zablotsky Vibrator indicator for turboengine rotor blading
US3514212A (en) * 1968-06-11 1970-05-26 Us Air Force Incipient stall sensor
US3677000A (en) * 1970-04-27 1972-07-18 Faulkner C Thomson System for the detection and control of compressor stall
US4153388A (en) * 1976-04-30 1979-05-08 Sulzer Brothers Limited Method and apparatus for monitoring the state of oscillation of the blades of a rotor
US4067661A (en) * 1976-10-01 1978-01-10 Caterpillar Tractor Co. Thermally compensated variable turbine nozzle position indicator
US10100663B2 (en) 2015-06-04 2018-10-16 Rolls-Royce Plc Actuation arrangement

Also Published As

Publication number Publication date
FR978207A (fr) 1951-04-11
BE486585A (en(2012))
GB641998A (en) 1950-08-23

Similar Documents

Publication Publication Date Title
US2677273A (en) Turbine, compressor, or like rotary machine having a pivoted indicator blade responsive to operating conditions
US3876326A (en) Surge control system
US4955269A (en) Turbine blade fatigue monitor
Hiett et al. Paper 7: Experiments concerning the aerodynamic performance of inward flow radial turbines
CA1331491C (en) Shrouded turbine blade vibration monitor
EP0029736B1 (en) Method of diagnosis of operating conditions of bearing and apparatus therefor
US3950985A (en) Method of and apparatus for monitoring the durability of components of thermal power plants
EP0327865B1 (en) Turbine blade fatigue monitor
EP1795861A1 (en) Multi-range clearance measurement system and method of operation
CN109141794B (zh) 一种旋转叶片激振测试装置及系统
CN103775139A (zh) 涡轮发动机的间隙控制系统及涡轮发动机的间隙控制方法
WO2019022852A1 (en) VEHICLE VIBRATION MONITORING DEVICE WITH AUTOMATIC ADJUSTING SENSOR FEED MECHANISM
CN114117862A (zh) 一种发动机整机振动测点选取方法和系统
CN102095561B (zh) 一种大型汽轮机转动部件脱落故障定位方法
US3025670A (en) Method and apparatus for detecting, measuring and controlling the temperature of gas turbine engines
US2745969A (en) Turbo-machines
CN212254562U (zh) 汽轮机动叶片振动监测系统
CN206190737U (zh) 汽轮机推力瓦轴向推力测量装置
CA2962702A1 (en) Rotating machine and installation for converting energy comprising such a machine
JP3715352B2 (ja) 翼温度監視装置およびガスタービン
GB1245421A (en) Testing materials
CN114942119A (zh) 高温高速旋转叶轮机械瞬态流场测试系统
Neal et al. Operating Characteristics of the 100,000-Kw Essex Turbine Generator
Łagodzinski et al. Application of a compliant foil bearing for the thrust force estimation in the single stage radial blower
Brandstetter et al. ECL5/CATANA: Comparative analysis of advanced blade vibration measurement techniques