US3243158A - Turbine construction - Google Patents

Turbine construction Download PDF

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Publication number
US3243158A
US3243158A US337905A US33790564A US3243158A US 3243158 A US3243158 A US 3243158A US 337905 A US337905 A US 337905A US 33790564 A US33790564 A US 33790564A US 3243158 A US3243158 A US 3243158A
Authority
US
United States
Prior art keywords
casing
ring
turbine
blades
containment
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
US337905A
Other languages
English (en)
Inventor
James M Desmond
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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
Priority to NL134135D priority Critical patent/NL134135C/xx
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
Priority to US337905A priority patent/US3243158A/en
Priority to FR1722A priority patent/FR1435869A/fr
Priority to GB1495/65A priority patent/GB1093312A/en
Priority to NL6500415A priority patent/NL6500415A/xx
Priority to CH53065A priority patent/CH460450A/fr
Priority to DE1965U0011371 priority patent/DE1476916B2/de
Priority to BE658332D priority patent/BE658332A/xx
Priority to SE524/65A priority patent/SE305775B/xx
Application granted granted Critical
Publication of US3243158A publication Critical patent/US3243158A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D21/045—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

Definitions

  • This invention relates to a gas turbine and particularly to a containment for parts of a turbine disc or blades in the event of failure of the rotor.
  • One feature of the invention is a ring surrounding the gas path through the turbine and in a position to be engaged by fragments in the event of a rotor failure.
  • Another feature is a ring made of a flexible resilient material and so mounted as to absorb the large amounts of energy in the yfragments so that they will not break through the surrounding casing.
  • One feature of the invention is the support of the containment ring or rings so that they may be distorted when engaged by fragments of the rotor thereby having a greater absorptive capacity.
  • Another feature is the support of the containment ring or rings within and in spaced relation to the casing and in such a way that the ring is normally held in concentric relation to the casing.
  • One feature of the invention is the support of the containment ring in such a way that the latter may also support the usual shroud ring surrounding the row of turbine blades.
  • FIG. 1 is a longitudinal sectional view through a part of the turbine, the section in part being along the lines 1 1 of FIG. 2 and FIG. 3.
  • FIG. 2 is a developed detail substantially along the line 2 2 of FIG. l with a portion broken away.
  • FIG. 3 is a developed detail substantially along the Aline 3 3 of FIG. 1.
  • FIG. 4 is a fragmentary view similar to FIG. 1 along a section line 4 4 of FIG. 2.
  • FIG. 5 is a fragmentary view similar to FIG. 1 substantially along the line 5 5 of FIG. 3.
  • the turbine has a casing 2 which surrounds the turbine rotor 4.
  • the rotor includes a disc, not shown, to the periphery of which a plurality of blades 6 are attached.
  • a turbine of the basic construction shown in this application is described in the patent to Savin 2,747,- 367.
  • a forward portion 8 of the casing surrounds and supports a row of turbine vanes 10 defining nozzles through which gas flows to impinge on the blades for turning the rotor.
  • the attachment of the vanes within the casing portion 8 is not a part of the present invention.
  • a containment ring 12 Surrounding and in radial alignment with the row of blades 6 is a containment ring 12 in the form of a cylinder concentric to and spaced radially inwardly from the casing 2 to constitute a lining for the casing.
  • An annular spring 14 located between the containment ring and the casing serves to hold the containment ring in concentric position.
  • the spring 14 may be held in place by a spacer ring 16 attached to the ring 14 and resting on the inner periphery of the casing.
  • the ring 16 has a radial flange 18 engaging with a ange 20 projecting inwardly from the casing 2 to locate the ring 16 axially in the caslng.
  • a shroud ring 22 is supported in concentric relation to the containment ring 12 and in radial alignment with the turbine blades.
  • the shroud ring has radially outwardly extending lugs 26 at its forward end to engage in radial grooves 2S on a disc 30.
  • the shroud ring has other lugs 32, FIG, 4, at its rearward end engaging the inner ends of radial notches 34 formed in the inwardly projecting ange 20, as shown in FIG. 3.
  • the inner end of the flange 20 has a rearwardly extending cylindrical flange 35 thereon, as shown, interrupted where the radial notches 34 occur.
  • the disc 30 is clamped between the casing 2 and the portion 8 and serves to engage the outer shroud 36 on each of the Vanes 10 to hold the vanes in axial position.
  • the grooves 28 also engage with cooperating lugs 38 on the forward end of the containment ring 12 thereby further serving to hold the containment ring in concentric relation to the casing although permitting movement of the ring radially outward at any particular portion of the ring in the event that the shroud ring and thence the containment ring is hit by fragments of the rotor in the event of ruptura
  • the rearward end of the containment ring also has lugs 40 which engage with alternate notches 34 in the inwardly extending ange 20, as shown in FIGS. l and 2.
  • concentric containment rings 42 and 44 Extending downstream from the iiange 20 and located within the casing 2 are concentric containment rings 42 and 44, the latter being smaller in diameter and located in spaced radial relation to the larger ring 42.
  • the larger ring 42 is radially spaced inwardly of the casing and constitutes an extension of the lining for the casing.
  • the forward end of the rings 42 and 44 have lugs 46 and 48, FIG. 4, respectively, which engage with alternate notches 34, fitting, as will be apparent, in the notches not occupied by the lugs 40 of ring 12.
  • the forward end of the containment ring 44 has a notch 50 in one corner to receive the trailing edge of the lugs 33 on the shroud ring 22 and the trailing edge of the flange 35 so that this containment ring 42 also functions as an extension of the outer wall of the gas path through the turbine.
  • a supporting disc 52 clamped between a ange 54 on the casing and a cooperating downstream portion 56 of the casing.
  • the disc 52 has a projecting rib 58 thereon having notches 60 therein cooperating with lugs 62 on the containment ring 42 and lugs 64 on the containment ring 44.
  • the containment rings 12, 42 and 44 are supported radially inwardly of the casing in such a way that should the turbine rotor fail and fragments thereof are thrown outwardly by centrifugal force, they will irnpinge on either the shroud ring 22 or the containment ring 44. Because of the energy in these fragments they may carry through the shroud ring 22 and into contact with the ring 12 or into or through the ring 44 to engage the ring 42.
  • These rings 12, 42 and 44 are made of a tough resilient material preferably steel although they might well be made of a non-metallic material such as Fiberglas.
  • this construction is a safety feature for protecting the structure surrounding the turbine. If it is incorporated in a turbine aircraft engine it will protect the remainder of the aircraft from damage by the fragments from the engine or if in a stationary Powerplant ⁇ it will protect personnel or other machinery or apparatus located near to the powerplant.
  • an outer casing a row of vanes within the casing, a row of blades within the casing downstream of the vanes, a rotor disc on which the blades are mounted, a shroud ring located at the periphery of the row of blades and spaced radially in- Ward of the casing, and a containment ring located Within the casing between the casing and the shroud ring and in spaced radial relation thereto in a position to be engaged by fragments of the blades or the disc in the event of failure, said containment ring being mounted so as to yield radially into contact with the casing.
  • a turbine construction as in claim 1 in which said casing has a set of radial notches thereon and said ring has lugs at one edge to engage with the notches on the casing.
  • a turbine construction as in claim 1 in which a second ring is provided substantially in axial alignment with the first ring and downstream thereof, said second ring being within and spaced radially of the outer casing.
  • a turbine construction as in claim 4 in which the rst and second rings have lugs at adjacent edges engaging in notches in a rib on the casing to hold the rings in axial alignment.
  • a turbine construction including, a casing having a varied stator therein, a rotor including a disc having a row of blades on its periphery mounted for rotation within the casing, a shroud ring in the form substantially of a cylinder located within and spaced from the casing and in radial alignment with the blades, and a lining for a part of the casing to protect it from fragments in the event of failure lof the rotor, said lining including at least one containment ring of substantially cylindrical configuration located between the shroud ring and the casing and in radially spaced relation to both, said containment ring and said casing having cooperating means located at each end of the ring for supporting said ring in radially spaced relation to and Within the casing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US337905A 1964-01-15 1964-01-15 Turbine construction Expired - Lifetime US3243158A (en)

Priority Applications (9)

Application Number Priority Date Filing Date Title
NL134135D NL134135C (ru) 1964-01-15
US337905A US3243158A (en) 1964-01-15 1964-01-15 Turbine construction
GB1495/65A GB1093312A (en) 1964-01-15 1965-01-13 Improvements in or relating to turbine construction
FR1722A FR1435869A (fr) 1964-01-15 1965-01-13 Amélioration dans la construction de turbine
NL6500415A NL6500415A (ru) 1964-01-15 1965-01-14
CH53065A CH460450A (fr) 1964-01-15 1965-01-14 Turbine à gaz
DE1965U0011371 DE1476916B2 (de) 1964-01-15 1965-01-15 Auffangvorrichtung zum Auffangen von Laufschaufel-Bruchstücken in einer Axialturbine
BE658332D BE658332A (ru) 1964-01-15 1965-01-15
SE524/65A SE305775B (ru) 1964-01-15 1965-01-15

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US337905A US3243158A (en) 1964-01-15 1964-01-15 Turbine construction

Publications (1)

Publication Number Publication Date
US3243158A true US3243158A (en) 1966-03-29

Family

ID=23322518

Family Applications (1)

Application Number Title Priority Date Filing Date
US337905A Expired - Lifetime US3243158A (en) 1964-01-15 1964-01-15 Turbine construction

Country Status (8)

Country Link
US (1) US3243158A (ru)
BE (1) BE658332A (ru)
CH (1) CH460450A (ru)
DE (1) DE1476916B2 (ru)
FR (1) FR1435869A (ru)
GB (1) GB1093312A (ru)
NL (2) NL6500415A (ru)
SE (1) SE305775B (ru)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3295751A (en) * 1965-04-21 1967-01-03 United Aircraft Corp Compressor stator shroud arrangement
US3387820A (en) * 1965-05-24 1968-06-11 Continental Aviat & Engineerin Turbine engine construction
US3391904A (en) * 1966-11-02 1968-07-09 United Aircraft Corp Optimum response tip seal
US3428129A (en) * 1966-12-27 1969-02-18 Mobil Oil Corp Vertical fracture control
US3836279A (en) * 1973-02-23 1974-09-17 United Aircraft Corp Seal means for blade and shroud
US4295787A (en) * 1979-03-30 1981-10-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Removable support for the sealing lining of the casing of jet engine blowers
US4460311A (en) * 1980-05-24 1984-07-17 MTU Motogren-Und Turbinen-Union Apparatus for minimizing and maintaining constant the blade tip clearance of axial-flow turbines in gas turbine engines
US5395211A (en) * 1994-01-14 1995-03-07 United Technologies Corporation Stator structure for a rotary machine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2574476B1 (fr) * 1984-12-06 1987-01-02 Snecma Carter de retention pour soufflante de turboreacteur

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR975879A (fr) * 1948-12-06 1951-03-12 Const Et D Equipements Mecaniq Perfectionnement dans la construction des cylindres pour turbines à gaz
GB790854A (en) * 1954-12-16 1958-02-19 Rolls Royce Improvements in or relating to axial-flow fluid machines
US2987296A (en) * 1957-12-02 1961-06-06 Bendix Corp Safety device for starter turbine
US2999667A (en) * 1956-09-28 1961-09-12 Rolls Royce Protective arrangement for use with apparatus or machines having rotating parts
US3146992A (en) * 1962-12-10 1964-09-01 Gen Electric Turbine shroud support structure

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR975879A (fr) * 1948-12-06 1951-03-12 Const Et D Equipements Mecaniq Perfectionnement dans la construction des cylindres pour turbines à gaz
GB790854A (en) * 1954-12-16 1958-02-19 Rolls Royce Improvements in or relating to axial-flow fluid machines
US2999667A (en) * 1956-09-28 1961-09-12 Rolls Royce Protective arrangement for use with apparatus or machines having rotating parts
US2987296A (en) * 1957-12-02 1961-06-06 Bendix Corp Safety device for starter turbine
US3146992A (en) * 1962-12-10 1964-09-01 Gen Electric Turbine shroud support structure

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3295751A (en) * 1965-04-21 1967-01-03 United Aircraft Corp Compressor stator shroud arrangement
US3387820A (en) * 1965-05-24 1968-06-11 Continental Aviat & Engineerin Turbine engine construction
US3391904A (en) * 1966-11-02 1968-07-09 United Aircraft Corp Optimum response tip seal
US3428129A (en) * 1966-12-27 1969-02-18 Mobil Oil Corp Vertical fracture control
US3836279A (en) * 1973-02-23 1974-09-17 United Aircraft Corp Seal means for blade and shroud
US4295787A (en) * 1979-03-30 1981-10-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Removable support for the sealing lining of the casing of jet engine blowers
US4460311A (en) * 1980-05-24 1984-07-17 MTU Motogren-Und Turbinen-Union Apparatus for minimizing and maintaining constant the blade tip clearance of axial-flow turbines in gas turbine engines
US5395211A (en) * 1994-01-14 1995-03-07 United Technologies Corporation Stator structure for a rotary machine

Also Published As

Publication number Publication date
DE1476916B2 (de) 1970-11-26
DE1476916A1 (de) 1970-08-06
CH460450A (fr) 1968-07-31
SE305775B (ru) 1968-11-04
GB1093312A (en) 1967-11-29
BE658332A (ru) 1965-04-30
FR1435869A (fr) 1966-04-22
NL134135C (ru)
NL6500415A (ru) 1965-07-16

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