US2930188A - Gas-turbine engine with failure-operated control means - Google Patents

Gas-turbine engine with failure-operated control means Download PDF

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Publication number
US2930188A
US2930188A US693297A US69329757A US2930188A US 2930188 A US2930188 A US 2930188A US 693297 A US693297 A US 693297A US 69329757 A US69329757 A US 69329757A US 2930188 A US2930188 A US 2930188A
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United States
Prior art keywords
pressure
tube
chamber
gas
turbine
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Expired - Lifetime
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US693297A
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English (en)
Inventor
Haworth Lionel
Mclean Donald
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Rolls Royce PLC
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Rolls Royce PLC
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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
    • F01D21/06—Shutting-down
    • 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
    • F01D21/14—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages

Definitions

  • This invention relates to gas-turbine engines of the kind which comprises a turbine rotor and a coaxial driven member such as a compressor rotor, or the reduction gear of a propeller, which are interconnected by 'a driving shaft.
  • gas-turbine engines will be referred to as being of the class specified.
  • This invention has for an object to provide control means which responds rapidly to shaft failure to prevent such overspeeding.
  • a tube or theequivalent is provided which extends within the'd'riving shaft and is drivingly connected to the shaft atspaced locations'o'ns, one such location being in the region of the load, e.g. the compressor rotor, and another such location being in the region of the turbine rotor, said tube or equivalent being fed with a fluid under pressure thereby to provide a pressurised chamber, which chamber is connected to pressure-responsive means controlling the supply of fuel to the engine, the arrangement being such that in the event of fracture of the shaft said tube or the equivalent is also fractured, resulting in reduction of pressure on the pressure-sensitive means thereby to reduce the fuel supply to the engine.
  • a gas-turbine engine of the class specified has a rotor system which includes a hollow driving shaft and a tube extending through the shaft, the tube being drivingly connected to the rotor system adjacent the turbine and adjacent the load and the wall of the tube being weakened at a' location between said driving connections so that the tube fractures at said location on failure of the shaft, and the tube having within it means defining with the weakened portion of the wall a chamber of limited volume having a restricted inlet, and comprises means to supply pressure fluid to the chamber through said inlet, and means responsive to the pressure within the chamber and operative on fall of pressure within the chamber to cut down the fuel supply to the engine.
  • means is connected to the chamber to permit any air (or other gas) separating from the pressure liquid to be led away from the chamber.
  • any air under pressure in the chamber will reduce the rate of response of the control and thus it is desirable that the chamber be bled of free air (or other gas).
  • the tube is fed with lubricating oil under pressure and the tube is also employed as an oil distributor for the bearings of the rotor system.
  • FIG. 1 illustrates diagrammatically a simple gas turbine engine and shows parts of the engine lubricating and fuel systems and a failure control arrangement. of this invention
  • Figure 2 shows in greater detail a construction bodying features illustrated in Figure 1.
  • the engine comprises an axial-flow compressor having a statorcasing 10a and a rotor 10b, combustion equipment 11 which receives air compressed in the compressor and has fuel fed to it through injector nozzles 12, and a turbine havinga casing 13a and rotor 13b, which turbine receives the com; bustion products from the combustion equipment 11.
  • the turbine rotor 13b is drivingly connected to the compressor rotor 10b by a hollow driving shaft 14.
  • the fuel system is of any known or convenient kind and that illustrated comprises a multi-piston swash-plate pump 15 which is engine driven and which is controlled as to its delivery by a servo motor under control of a unit 16.
  • the pump draws in fuel through suction pipe” -17 and delivers through pipe 18 past a throttle 19 to a manifold 20 from which branches lead to the injector nozzles 12.
  • the servo motor controlling the pump 15 comprises a piston 21 separating two pressure spaces 22, 23, where? of the space 22 is directly connected through a duct 24 with the delivery pipe 18 of the pump and of which the" space 23 is connected to the delivery of the pump through a restricted orifice 25.
  • a spring 26 is accommodated within the space 23 and urges the piston 21 to a position corresponding to maximum fuel delivery of the pump.
  • the pressure space 23 also has connected to it a bleed pipe 27, the opposite end of which is controlled by a half ball valve element 28 forming part of the control unit 16. It will be clear that when the valve element 28 lifts a greater flow occurs through the bleed her.
  • the lever 30 carries the valve element 28 at one:
  • the fuel delivery pressure tends to cause a decrease in the fuel delivery of the pump 15 and that a'fall'in the fuel delivery pressure tends to cause an increase in the.
  • the opposite end of the lever 30 is loaded in the sense to lift the valve element 28 off the'end of the pipe-27 by an evacuated capsule 35 and the chamber nouns-gor the capsule is open to atmosphere through port 36.
  • the lubricating system of the engine comprises a lubricating oil pump 37 delivering oil through a pipe 38 to a muff 39 from which the pressure oil is fed into a tube 40 rotating with the rotor system of the engine.
  • the oil may be fed from the tube to the bearings of the rotor system in any convenient manner.
  • the tube 40 is drivingly connected with the rotor system by two sets of splines, of which splines 41 drivingly connect one end of the tube to the compressor rotor 10b and the other set of splines 42 drivingly connect the opposite end of the tube to the turbine rotor 13!), preferably to a stub shaft 43 projecting downstream from the turbine disc into a central bullet 44 of the turbine exhaust assembly.
  • a constriction 45 is formed intern-ally of the tube at a position remote from the oil supply muff 39 so as to define with the wall of the tube a chamber 46' of limited capacity having a restricted oil inlet.
  • the portion of the tube wall defining the chamber 46' is provided with a shear neck in the form of -a helical groove 47 and thus it will be clear that in the event of failure of the dri-ving shaft 14 the tube 40 will be quickly fractured in the region of the shear neck 47.
  • the chamber 46 is placed in communication with pressure-responsive means through ducting 48 ard there is also provided a deaerator 49 so that any air separating from the lubricating oil within the chamber is bled off from the chamber.
  • the pressure-responsive means comprises a casing 50 divided into three chambers 53, 54, 58 by a flexible diaphragm 51 and a rigid wall 52.
  • the conduit 48 opens into the chamber 53 so that the diaphragm 51 is subjected on one side to the pressure within the chamber 46 and the chamber 54 on the opposite side of the diaphragm 51 is open to atmosphere through polts 55.
  • a spring 56 is accommodated within the chamber 54 and loads the diaphragm 51 in opposition to the fluid pressure in chamber 53.
  • the diaphragm has secured centrally to it a stem 57 which passes through the wall 52 into the third chamber 58 and the stem 57 carries at its lower end a half ball valve element 59 co-operating with the end of a branch 60 from the bleed pipe 27.
  • a drain pipe 61 leads from the chamber 58, for example back to the suction side of the pump 15.
  • a manually-controlled lever 50a is provided on the casing 50 to permit the half-ball valve 59 to be held closed while oil pressure is building up in the chamber 53 during starting.
  • the stationary structure has a closed space 64 defined within it by means of a cup member 63 and the cup member supports a flanged plug 65 the stem of which projects into and seals the bore of the tube 40.
  • the plug 65 has a central bore 66 leading from within the chamber 46 to the closed space 64 into which also opens one end of the ducting 48.
  • an air bleed duct 67 leads to a cavity 68 in the stationary structure and the cavity contains a sleeve 69 engaged by a landed plug 70 providing a restricted passage for air separating from the lubricant in operation.
  • the plug 65 is retained axially in position in the cup member 63 by a flange 65a on the plug being sandwiched between an internal flange 63a of the cup member and a plate 71 retained by a spring circular retaining clip 71a.
  • the lubricating oil pressure within the space 64 pressure loads the flange 65a against the flange 63a.
  • the plug 65 is free to rotate relatively to the stationary structure and to the tube 40.
  • a com.- pound gas-turbine engine comprises a low-pressure compressor, a high-pressure compressor, a high-pressure turbine drivingly connected to the high-pressure compressor and the low-pressure turbine drivingly connected to the low-pressure compressor and also through a reduction gear to the propeller where such is provided.
  • the low-pressure driving shaft coaxially within the high-pressure driving shaft and in applying the invention to such an engine the tube associated with the failure control may be accommodated within the lowpressure shaft and be drivingly connected to the lowpressure turbine rotor and the low-pressure compressor rotor.
  • the lubricating oil may be fed from the tube to inter-shaft bearings.
  • a gas-turbine engine of the class specified comprising a fuel supply system and a pressure fluid source separate from the fuel system and further comprising a tube or the equivalent which extends within the driving shaft and is drivingly connected to the shaft at spaced locations, one such location being in the region of the load, and another such location being in the region of the turbine rotor, said tube or equivalent being fed with fluid under pressure from said pressure fluid source thereby to provide a pressurised chamber, which chamber is connected to pressure-responsive means controlling the supply of fuel to the engine, the arrangement being such that in the event of fracture of the shaft said tube or the equivalent is also fractured, resulting in reduction of pressure on the pressure-sensitive mean thereby to reduce the fuel supply by the fuel supply means to the engine.
  • a gas-turbine engine of the class specified comprising a fuel supply system, the rotor system including a hollow driving shaft and a tube extending through the shaft, the tube being drivingly connected to the rotor system adjacent the turbine and adjacent the load and the wall of the tube being weakened at a location between said driving connections so that the tube fractures at said location on failure of the shaft, and the tube having within it means defining with the weakened portion of the wall a. chamber of limited volume having a restricted inlet, and comprising also pressure fluid supply means separate from said fuel system and connected to supply pressure fluid to the chamber through said inlet,
  • a gas-turbine engine wherein Y the turbine has a shaft extension on the side thereof remote from the load, the tube extending in said extension, and the first driving connection between the tube' and the rotor system being through said shaft extension, and the restricted inlet and weakened portion of the tube being adjacent the turbine.
  • a gas-turbine engine comprising also means connected to the chamber to permit gas separating from the pressure liquid to be led away from the chamber.
  • a gas-turbine engine as claimed in claim 2, comprising means effecting the fuel supply to the engine, which means includes a servo-mechanism controlling the fuel delivery to the engine and having a servo-fluid bleed pipe flow through which controls the operation of the servo-mechanism, and wherein the pressure-responsive means actuates a bleed valve at an outlet from the bleed pipe in the sense to decrease the fuel delivery when the pressure to which the pressure-responsive means is subjected falls.
  • the pressure-responsive means comprises a flexible diaphragm separating a pair of chambers, the bleed valve being carried by the diaphragm, one of the chambers separated by the diaphragm being connected to the chamber within said tube so that the diaphragm is loaded in one sense by the pressure in the chamber in the tube and the diaphragm being loaded in' the opposite sense by a spring contained in the other of the pair of chambers, the said other chamber being connected to atmosphere.
  • a gas turbine engine comprising a rotor system including a turbine rotor, a co-axial driven member, a hollow driving shaft drivingly interconnecting the turbine rotor and the driven member and a hollow shaft extension on the side of the turbine rotor remote from the driven member, a tube extending from adjacent the driven member through a driving shaft and the shaft extension and having an end portion projecting beyond the end of the shaft extension, a first driving connection interconnecting the tube and shaft extension, a second driving connection interconnecting the tube and the rotor system adjacent the driven member, the tube having a weakened wall portion 6 the second driving connection, means to supply pressure fluid to said tube at its end adjacent the second driving connection, stationary structure having a chamber therein, a plug having a bore therein, the plug being rotationally mounted in the stationary structure and engaging the projecting end portion of the tube with freedom for relative rotation thereto, the bore of the plug interconnecting the tube and the chamber, fuel supply means delivering fuel to the engine, and pressure-responsive means connected to said chamber to respond to the pressure
  • a gas-turbine engine according to claimlO comprising also means connected to said chamber to conduct gas separating from the pressure liquid away'from said chamber.
  • A' gas turbine engine according to claim 11, wherein said means to conduct gas away from said chamber comprisesv a restricted outlet from the upper side of the chamber.
  • a gas turbine engine according to claim 10, comprising bearings supporting said rotor system in said sta tionary structure, said tube being employed as an oil distributor for said bearings and said means supplying pressure liquid to the tube being, adapted to supply lubricating oil to the tube.
  • the fuel supply means includes a servomechanism controlling the fuel delivery to the engine and having a servo-fluid bleed pipe flow through which controls the operation of the servo-mechanism, and wherein the pressure-responsive means actuates a bleed valve at an outlet from the bleed pipe in the sense to decrease the fuel delivery when the pressure to which the pressureresponsive means is subjected, falls.
  • the pressure-responsive means comprises a flexible diaphragm separating a pair of chambers, the bleed valve being carried by the diaphragm, one of the chambers separated by the diaphragm being connected to the chamber within said tube so that the diaphragm is loaded in one sense by the pressure in the chamber in the tube and the diaphragm being loaded in the opposite sense by a spring contained in the otherof the pair of chambers,

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Control Of Turbines (AREA)
US693297A 1956-11-08 1957-10-30 Gas-turbine engine with failure-operated control means Expired - Lifetime US2930188A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB34217/56A GB837309A (en) 1956-11-08 1956-11-08 Improvements in or relating to gas-turbine engines

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US2930188A true US2930188A (en) 1960-03-29

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US (1) US2930188A (fr)
DE (1) DE1072014B (fr)
FR (1) FR1185633A (fr)
GB (1) GB837309A (fr)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3159166A (en) * 1961-10-16 1964-12-01 Gen Motors Corp Engine safety control
US3498282A (en) * 1967-12-21 1970-03-03 Donald P Dattilo Mechanism for automatically stopping internal combustion engines
US4037404A (en) * 1975-07-09 1977-07-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Coupling device for gas turbine engine
US4389984A (en) * 1981-03-26 1983-06-28 Destrampe Terry G Post-shutdown coolant-supply device
US4473998A (en) * 1982-06-30 1984-10-02 Rolls-Royce Limited Gas turbine engines
US5953901A (en) * 1993-12-06 1999-09-21 Bmw Rolls-Royce Gmbh Mechanical fuel shut-off system for a gas turbine
WO2003093652A2 (fr) * 2001-11-14 2003-11-13 Honeywell International Inc. Systeme de detection de rupture d'arbre dans une turbine a gaz
US20070256404A1 (en) * 2005-09-26 2007-11-08 Pratt & Whitney Canada Corp. Method of adjusting a triggering clearance and a trigger
US20090235630A1 (en) * 2008-03-20 2009-09-24 Norris James W Non-interrupted oil supply for gas turbine engine
US9291070B2 (en) 2010-12-03 2016-03-22 Pratt & Whitney Canada Corp. Gas turbine rotor containment
EP3382160A1 (fr) * 2017-03-28 2018-10-03 Ge Avio S.r.l. Système de rotation de moteur à turbine à gaz et sa méthode de fonctionnement
US10316689B2 (en) 2016-08-22 2019-06-11 Rolls-Royce Corporation Gas turbine engine health monitoring system with shaft-twist sensors

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2551429A (en) * 1948-11-19 1951-05-01 Ingersoll Rand Co Safety trip device for motors responsive to temperature, speed, and pressure
US2676458A (en) * 1951-09-17 1954-04-27 Boeing Co Gas turbine combined lubricating, and fuel supply system having centrifugal means topurify and circulate fuel
US2693248A (en) * 1950-05-03 1954-11-02 Gen Motors Corp Lubrication system

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2551429A (en) * 1948-11-19 1951-05-01 Ingersoll Rand Co Safety trip device for motors responsive to temperature, speed, and pressure
US2693248A (en) * 1950-05-03 1954-11-02 Gen Motors Corp Lubrication system
US2676458A (en) * 1951-09-17 1954-04-27 Boeing Co Gas turbine combined lubricating, and fuel supply system having centrifugal means topurify and circulate fuel

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3159166A (en) * 1961-10-16 1964-12-01 Gen Motors Corp Engine safety control
US3498282A (en) * 1967-12-21 1970-03-03 Donald P Dattilo Mechanism for automatically stopping internal combustion engines
US4037404A (en) * 1975-07-09 1977-07-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Coupling device for gas turbine engine
US4389984A (en) * 1981-03-26 1983-06-28 Destrampe Terry G Post-shutdown coolant-supply device
US4473998A (en) * 1982-06-30 1984-10-02 Rolls-Royce Limited Gas turbine engines
US5953901A (en) * 1993-12-06 1999-09-21 Bmw Rolls-Royce Gmbh Mechanical fuel shut-off system for a gas turbine
WO2003093652A2 (fr) * 2001-11-14 2003-11-13 Honeywell International Inc. Systeme de detection de rupture d'arbre dans une turbine a gaz
WO2003093652A3 (fr) * 2001-11-14 2004-06-17 Honeywell Int Inc Systeme de detection de rupture d'arbre dans une turbine a gaz
US20070256404A1 (en) * 2005-09-26 2007-11-08 Pratt & Whitney Canada Corp. Method of adjusting a triggering clearance and a trigger
US7654093B2 (en) 2005-09-26 2010-02-02 Pratt & Whitney Canada Corp. Method of adjusting a triggering clearance and a trigger
US20090235630A1 (en) * 2008-03-20 2009-09-24 Norris James W Non-interrupted oil supply for gas turbine engine
US8567564B2 (en) * 2008-03-20 2013-10-29 United Technologies Corporation Non-interrupted oil supply for gas turbine engine
US9291070B2 (en) 2010-12-03 2016-03-22 Pratt & Whitney Canada Corp. Gas turbine rotor containment
US10316689B2 (en) 2016-08-22 2019-06-11 Rolls-Royce Corporation Gas turbine engine health monitoring system with shaft-twist sensors
EP3382160A1 (fr) * 2017-03-28 2018-10-03 Ge Avio S.r.l. Système de rotation de moteur à turbine à gaz et sa méthode de fonctionnement
WO2018177942A1 (fr) * 2017-03-28 2018-10-04 Ge Avio S.R.L. Système de rotation pour moteur à turbine à gaz
CN110475946A (zh) * 2017-03-28 2019-11-19 通用电气阿维奥有限责任公司 燃气涡轮发动机转动系统
CN110475946B (zh) * 2017-03-28 2022-08-23 通用电气阿维奥有限责任公司 燃气涡轮发动机转动系统
US11536202B2 (en) 2017-03-28 2022-12-27 Ge Avio S.R.L. Gas turbine engine turning system

Also Published As

Publication number Publication date
GB837309A (en) 1960-06-09
DE1072014B (fr) 1959-12-24
FR1185633A (fr) 1959-08-03

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