WO1997001708A1 - Demarreur a turbine a gaz - Google Patents

Demarreur a turbine a gaz Download PDF

Info

Publication number
WO1997001708A1
WO1997001708A1 PCT/US1996/010903 US9610903W WO9701708A1 WO 1997001708 A1 WO1997001708 A1 WO 1997001708A1 US 9610903 W US9610903 W US 9610903W WO 9701708 A1 WO9701708 A1 WO 9701708A1
Authority
WO
WIPO (PCT)
Prior art keywords
reversing
turbine
ring
turbomachine
rotating blade
Prior art date
Application number
PCT/US1996/010903
Other languages
English (en)
Inventor
William C. Maier
Original Assignee
Dresser-Rand Company
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 Dresser-Rand Company filed Critical Dresser-Rand Company
Publication of WO1997001708A1 publication Critical patent/WO1997001708A1/fr

Links

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
    • F01D21/045—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 special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
    • F02C1/02—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being an unheated pressurised gas
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275—Mechanical drives
    • F02C7/277—Mechanical drives the starter being a separate turbine

Definitions

  • the present invention relates to high speed rotary machines, more particularly turbine type machines and improved designs for gas turbine starters .
  • a turbomachine having at least one turbine wheel rotatable about an axis, and having a circumferential edge.
  • Each wheel comprises a plurality of rotating blade rows, radially displaced from the axis and positioned along the circumferential edge.
  • Each blade row has a plurality of circumferentially spaced blades.
  • the turbomachine also includes a reversing ring comprising a retaining ring holding a reversing blade row with a plurality of circumferentially-spaced reversing blades extending radially inward from the retaining ring between adjacent blade rows of the turbine wheel.
  • the reversing ring is positioned at a location radially outward of the rotating blade rows with the reversing blade row being axially displaced from adjacent rotating blade rows to permit clearance for rotation of said turbine wheel.
  • the reversing ring is positioned to receive flow from an adjacent first rotating blade row and to direct the flow to an adjacent second rotating blade row.
  • the retaining ring extends axially to an extent sufficient to cover the rotating blade rows.
  • a method for containing broken turbine part fragments in an operating turbomachine includes providing a turbomachine having at least one turbine wheel rotatable about an axis, and having a circumferential edge.
  • the wheel comprises a plurality of rotating blade rows, radially displaced from the axis and positioned along the circumferential edge.
  • Each blade row has a plurality of circumferentially spaced blades.
  • the method further includes retaining broken turbine part fragments with a reversing ring in close association to the rotating blade rows.
  • the reversing ring comprises a retaining ring holding a reversing blade row having a plurality of circumferentially-spaced reversing blades extending radially inward from the retaining ring between adjacent blade rows of said turbine wheel.
  • the reversing ring is positioned at a location radially outward of the rotating blade rows.
  • the reversing blade row is axially displaced from adjacent rotating blade rows to permit clearance for rotation of the turbine wheel and is positioned to receive flow from an adjacent first rotating blade row to direct the flow to an adjacent second rotating blade row.
  • the retaining ring extends axially to an extent sufficient to cover the rotating blade rows.
  • FIG. 1 is a frontal view of a turbine starter in accordance with the present invention.
  • FIG. 2 is a side view of the turbine starter of FIG. 1.
  • FIG. 3 is a side cross-sectional view of the turbine starter.
  • FIG. 4 is an enlarged cross-sectional view of the turbine starter of FIG. 3 detailing the mounting fastener and the reversing ring.
  • FIGS. 1 and 2 show an inlet flange 31 to a trip valve housing 66, an outlet housing 47, and an outlet flange 32.
  • Turbine shaft 34 has an output flange portion 36 with gear-like teeth 38 circumferentially disposed on the flange portion 36.
  • a speed pickup sensor 40 senses the movement of the teeth 38 as the shaft 34 rotates relative to the rotationally fixed pickup sensor 40.
  • the pickup sensor 40 transmits impulses proportional to the relative rotational speed of the shaft 34 through wires 42 to a readout device or control system (not shown) .
  • a single circle of fastening bolts 48 is used to fasten the major structural components of the turbine 30 together.
  • Bolts 48 secure the inlet ring 44 to the nozzle ring 46 and the exhaust housing 47.
  • a nut and bolt assembly 54 is extended through mounting feet 50 to secure the mounting feet 50, the exhaust housing 47, the nozzle ring 46, and the inlet ring 44 together.
  • the mounting feet 50 support the turbine 30 on a foundation in a manner which prevents movement during turbine operation.
  • FIG. 3 shows a cross-sectional view of the turbine starter 30.
  • Arrows 60 and 62 show the direction of the motive fluid flow through the turbine inlet flange 31 and exhaust flange 32 respectively.
  • a trip valve assembly 65 is positioned within the trip valve housing 66.
  • the trip valve assembly 65 comprises a spring 67, a valve stem 68, valve head 64, and valve seat 70 formed into inlet ring 44.
  • the motive fluid is free to flow from inlet flange 31 in arrow direction 60 into the trip valve housing 66, past the trip valve head 64, through the valve seat 70, and into the inlet ring 44.
  • the motive fluid is distributed circumferentially to nozzle passages 74 positioned circumferentially around turbine shaft 35 in the nozzle ring 46.
  • the motive fluid is thus presented to the rotating blade rows 76, 78 and reversing blades 82 in such a manner as to extract angular momentum and impart it to the turbine output flange 36 via the turbine wheel 77 and the turbine shaft 34.
  • the valve head 64 moves axially toward the valve seat 70, assisted by the force of the spring 67, closing off the flow of motive fluid to the turbine wheel 77.
  • FIG. 4 provides an enlarged cross-sectional view of the flowpath area of the turbine turbine starter of FIG. 3.
  • the first 76 and second 78 rotating blade rows both comprise groups of airfoil-shaped blades positioned circumferentially around the circumferential edge of the turbine wheel 77.
  • the blade rows 76, 78 are axially displaced from one another allowing room for the reversing blades 82 to be positioned therebetween.
  • the turbine wheel 77, assembly including the rotating blade rows 76, 78 is displaced axially from the stationary nozzle passage 74 allowing a suitable running clearance.
  • a row of reversing blades 82 is positioned axially between blade rows 76 and 78 and is held in position by retaining ring 88.
  • the assembly of the reversing blades and the retaining ring are together referred to as the reversing ring of the turbine.
  • the blade rows 76, 78, and 82 are positioned relative to the nozzle passage 74 and shaped to transfer the maximum possible angular momentum from the motive fluid to the shaft 34 and the output flange 36.
  • the reversing blades 82 are secured to the retaining ring by a dovetail 86 formed at the radially outer end of the reversing blades 82 with a matching groove in the retaining ring 88.
  • the retaining ring completely covers the axial extent of the rotating blade rows 76, 78 and the turbine wheel 77.
  • the reversing ring is shown to be of a length from the turbine housing equal to at least a distance d; a length in excess of the distance from the axially most distal edges of the first rotor blade row 76, and the second rotor blade row 78. It is understood that the precise length of the reversing ring will depend upon machining and design constraints.
  • the mounting feet 50, of the turbine 30 secure the turbine to a suitable base (not shown) .
  • the mounting feet 50 are bolted with fasteners, such as through bolts 54 to the turbine 30.
  • the mounting feet 50 are bolted with a nut and bolt assembly 54 together with the exhaust housing 47, the nozzle ring 46, and the inlet ring 44.
  • Bolt assembly 94 secures the reversing ring 88 to the nozzle ring 46.
  • the motive fluid or gas is introduced to the turbine inlet flange 31.
  • the pressurized motive fluid flows through the inlet flange 31 to the trip valve housing 66 and around the trip valve head 64.
  • the motive fluid continues through the valve seat 70 into the inlet ring 44 and is channeled circumferentially around the inlet ring 44 to the nozzle passage 74 in the nozzle ring 46.
  • the motive fluid then contacts the first rotating blade row 76 transferring some angular momentum to the blade row 76 causing a torque on the turbine wheel 77.
  • the motive fluid next contacts and passes through the reversing blade row 82 and is redirected to the second rotating blade row 78 causing additional transfer of angular momentum to the turbine wheel 77.
  • the motive fluid is collected and exhausted through the exhaust housing 47 and out through the outlet flange 32.
  • the turbine design of the present invention requires the extension of the multifunctional reversing ring over the rotating blade rows far enough to facilitate both a reduction in windage loss, and fragment containment in the event of an internal failure.
  • the innovative implementation of a suitably strong retaining ring attached to the reversing blade row results in many advantages over known turbine designs. In this instance, should the turbine system fail, resulting in the fragmentation of turbine parts, including turbine rotor blades moving at high speeds due to centrifugal force, the fragments would be blocked, deflected or held by the reversing ring.
  • the retaining ring attached to the reversing blade row, or both the reversing blade row and the retaining ring (the reversing ring) can be made of a suitable carbon steel or steel alloy, selected to best deflect and/or trap and adhere to high velocity debris.
  • a suitable carbon steel or steel alloy selected to best deflect and/or trap and adhere to high velocity debris.
  • turbine casings may be made of lighter and potentially less expensive materials.
  • Making the reversing ring multifunctional can lead to the overall weight reduction of the turbine which may be important for certain applications, such as flight, etc.
  • the deletion of additional parts, coatings, materials, etc. used for fragment containment can reduce the overall turbine manufacturing cost.
  • the reversing ring extends from the turbine housing to a distance at least approximately equal to the distance from the inner edge of one turbine rotor blade to the outer edge of a second turbine rotor blade. This is shown in FIG. 4 as distance d. It is understood that this distance will vary depending on the machining and design constraints, but will generally be of a length at least approximately equal to or greater than that shown as distance d in FIG. 4, such that the axial extents of all rotating blades are adequately covered.
  • the important attribute of a projectile or fragment containment means in a turbine is its ductility and tensile strength.
  • carbon steel and steel alloys are preferred. It has been determined that the steel alloys which are well suited for use as reversing rings must endure operating temperatures in the range of from about -25 to 250° F. For operating temperatures above -20°F an ASTM A- 350 grade LF1 carbon steel is adequate. However, from -20°F to -50°F, a LF2 grade carbon steel is required. This second temperature range is that normally encountered in gas turbine starter operation.
  • a grade LF3 carbon steel may be used. All of these carbon steel and steel alloy grades require ductility testing values with Charpy V- notch energies in the range of from about 10 to about 20 ft.lbs., with from about 13 to about 15 ft .lbs. being preferred. Further, the LF2 carbon steel displays a tensile strength of from about 485 to about 655 MPa.
  • the steel alloy chosen will depend on the selected operating parameters of the turbine, and the properties of the motive material flowing through the turbine. Steel alloy grade LF2 has the following approximate chemical composition in terms of wt . % according to the ASTM A 350/A 350M-94 specification sheet regarding carbon and low alloy steel compositions:
  • the material chosen for use as the reversing ring may be selected for its physical properties such as ductility, yield strength, corrosion resistance, weight, cost, etc. In all applications, the material selected must produce a reversing ring which will not allow fragments to pass therethrough. In certain instances, it may be desirable for the reversing ring to alter its physical characteristics upon impact with the high speed fragment (i.e. melt slightly) , so as to actually have the fragment adhere to the ring. In this way, the fragment will be less likely to deflect into the path of the rotor blades, causing further damage.
  • the ring may also be coated or otherwise treated with an additional material or layer for certain specific purposes, as mentioned above, and as would be readily apparent to one skilled in the turbine field.
  • the reversing rings and turbines of the present invention have the additional advantage of reducing the numbers and types of parts which would need to be replaced upon high speed failure and blade fragmentation. Indeed the outer turbine casing or housing is not placed at risk due to the resilient and strong fragment containment capabilities of the reversing rings of the present invention.
  • one aspect of the present invention is the use of standardized commercially available pipe fittings for the trip valve housing 66 located near the turbine inlet flange 31.
  • Using standardized or readily commercially available parts avoids the significant designing, manufacturing costs and time delays which attend the use of custom housings. This significantly reduces the overall manufacturing cost of the turbine engines, especially turbine engines used as turbine engine starters which are in use for only a relatively short time.
  • fasteners such as through bolts, screws, rivets, etc.
  • the speed pickups of the present invention are associated to contact the teeth on the flange of the shaft to determine the rotational speed of the turbine shaft.
  • the speed pickups do not contact the teeth of the flange, but are positioned to be able to "read" the speed of the flange teeth, without contact, and determine the rotational speed of the turbine shaft.
  • Magnetic or photo-electric pickups may be used as would be readily apparent to one skilled in the field.
  • the present invention is especially useful for smaller, slower turbines used to start larger and faster turbines.
  • the starter turbines generally move at speeds of up to about 4000 rpm. While the present invention is particularly suited for turbines having velocity compounded stages, it is understood that the present invention may be directed toward single stage and other types of turbomachinery.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une turbomachine comportant une roue de turbine (77) qui peut tourner autour d'un axe et qui possède un bord circonférentiel. Ladite roue de turbine comporte une pluralité de grilles d'aubes profilées (78) rotatives, décalées radialement par rapport à l'axe et disposées le long du bord circonférentiel, chaque grille d'aubes profilées comportant une pluralité d'aubes espacées suivant la circonférence ainsi qu'un anneau d'inversion (82) comportant un anneau de retenue (88) maintenant une grille d'aubes d'inversion. La grille d'aubes d'inversion (82) a une pluralité d'aubes d'inversion espacées suivant la circonférence, disposées radialement vers l'intérieur à partir de l'anneau de retenue entre des grilles d'aubes adjacentes de la roue de turbine, et positionnées radialement à l'extérieur des grilles d'aubes rotatives. La grille d'aubes d'inversion (82) est axialement décalée par rapport aux grilles d'aubes rotatives adjacentes de façon à ménager un dégagement pour la rotation de ladite roue de turbine, et est positionnée de façon à recevoir le flux d'une première grille d'aubes rotative adjacente et de façon à diriger le flux vers une seconde grille d'aubes rotative adjacente. L'anneau de retenue est conçu et axialement disposé sur une distance suffisante pour recouvrir les grilles d'aubes rotatives.
PCT/US1996/010903 1995-06-29 1996-06-26 Demarreur a turbine a gaz WO1997001708A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US49659995A 1995-06-29 1995-06-29
US08/496,599 1995-06-29

Publications (1)

Publication Number Publication Date
WO1997001708A1 true WO1997001708A1 (fr) 1997-01-16

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1996/010903 WO1997001708A1 (fr) 1995-06-29 1996-06-26 Demarreur a turbine a gaz

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WO (1) WO1997001708A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108035809A (zh) * 2017-11-06 2018-05-15 中国航空工业集团公司金城南京机电液压工程研究中心 一种空气涡轮起动机包容结构设计方法
EP3434879A1 (fr) * 2017-07-26 2019-01-30 Unison Industries LLC Démarreur de turbine à air

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US803950A (en) * 1905-01-10 1905-11-07 Franz Windhausen Elastic-fluid turbine.
US890635A (en) * 1906-02-14 1908-06-16 Gen Electric Elastic-fluid turbine.
US1307864A (en) * 1919-06-24 Steam-turbine
US2447942A (en) * 1944-12-05 1948-08-24 Rateau Soc Turbine distributor and nozzle
US2527446A (en) * 1948-09-17 1950-10-24 Westinghouse Electric Corp Turbine apparatus
US2651495A (en) * 1948-11-02 1953-09-08 Westinghouse Electric Corp Turbine inlet structure
US2966332A (en) * 1957-06-20 1960-12-27 Fairchild Engine & Airplane Overspeed control for turbine rotor
US3050282A (en) * 1958-04-03 1962-08-21 Gen Electric Turbine speed limiting arrangement
US4639188A (en) * 1984-12-04 1987-01-27 Sundstrand Corporation Turbine wheel containment

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1307864A (en) * 1919-06-24 Steam-turbine
US803950A (en) * 1905-01-10 1905-11-07 Franz Windhausen Elastic-fluid turbine.
US890635A (en) * 1906-02-14 1908-06-16 Gen Electric Elastic-fluid turbine.
US2447942A (en) * 1944-12-05 1948-08-24 Rateau Soc Turbine distributor and nozzle
US2527446A (en) * 1948-09-17 1950-10-24 Westinghouse Electric Corp Turbine apparatus
US2651495A (en) * 1948-11-02 1953-09-08 Westinghouse Electric Corp Turbine inlet structure
US2966332A (en) * 1957-06-20 1960-12-27 Fairchild Engine & Airplane Overspeed control for turbine rotor
US3050282A (en) * 1958-04-03 1962-08-21 Gen Electric Turbine speed limiting arrangement
US4639188A (en) * 1984-12-04 1987-01-27 Sundstrand Corporation Turbine wheel containment

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3434879A1 (fr) * 2017-07-26 2019-01-30 Unison Industries LLC Démarreur de turbine à air
CN108035809A (zh) * 2017-11-06 2018-05-15 中国航空工业集团公司金城南京机电液压工程研究中心 一种空气涡轮起动机包容结构设计方法

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