US3137478A - Cover plate assembly for sealing spaces between turbine buckets - Google Patents

Cover plate assembly for sealing spaces between turbine buckets Download PDF

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Publication number
US3137478A
US3137478A US209099A US20909962A US3137478A US 3137478 A US3137478 A US 3137478A US 209099 A US209099 A US 209099A US 20909962 A US20909962 A US 20909962A US 3137478 A US3137478 A US 3137478A
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US
United States
Prior art keywords
dovetail
bucket
turbine
cover plate
cover plates
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
US209099A
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English (en)
Inventor
William M Farrell
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.)
General Electric Co
Original Assignee
General Electric Co
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 NL295165D priority Critical patent/NL295165A/xx
Application filed by General Electric Co filed Critical General Electric Co
Priority to US209099A priority patent/US3137478A/en
Priority to GB24670/63A priority patent/GB1012066A/en
Priority to DEG38030A priority patent/DE1212108B/de
Priority to CH862063A priority patent/CH403402A/de
Priority to SE7610/63A priority patent/SE304417B/xx
Priority to FR941096A priority patent/FR1362926A/fr
Priority to NL63295165A priority patent/NL141273B/xx
Application granted granted Critical
Publication of US3137478A publication Critical patent/US3137478A/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Definitions

  • cover plates may be held at their radially innermost ends and thereby loaded in tension, as disclosed for example in US. Patent 2,998,959 issued to L. Hayworth et al. on September 5, 1961.
  • the local loading stress on the turbine Wheel caused by the cover plate is greater than that caused by the turbine bucket itself. This is because the bucket shank and bucket vane are of relatively thin crosssection and a plane taken radially through the shank and bucket normal to the turbine axis reveals a relatively small amount of metal acting upon the dovetail base in that plane. On the other hand, a radial planetaken through the cover plate normal to the turbine axis often reveals the local loading to be quite high in that plane.
  • the cover plate is held on the turbine rim by means of hooks or lugs holding the cover plate at its innermost end, or whether the cover plate loads the underside of the bucket platform, the load is ultimately transferred to the rim of the turbine wheel.
  • the increased local loading on the rim is more than often accompanied by bending moments, due to the fact that the cover plate is not radially in line with the point where it ultimately loads the turbine wheel rim. These bending moments serve to increase the local stress, and make the means of attachment of the cover plates a critical matter.
  • one object of the present invention is to provide improved cover plate structure and means of attachment therefor.
  • Still another object of the invention is to providean improved cover plate which, in addition to sealing olf flow between buckets, provides the additional functions of holding the turbine buckets against axial dislodgement from the wheel and serves as a mounting for flanges which form a circumferential sealing ring.
  • Yet another object of the invention is an improved means of locking turbine buckets together at the platforms when the wheel is rotating.
  • a more specific object of the invention is an improved cover plate, which is attached in a very eflicient manner to permit a low weight part, and which loads the turbine wheel rim in a uniform manner free from bending moments.
  • the invention is practiced by providing a segmented cover plate, eachsegment having a dovetail base which fits in an axially lengthened dovetail slot in the rotor rim together with the dovetail base of the long shank turbine bucket.
  • FIG. 1 is a portion of a turbine wheel, looking in an axial direction, showing several long Ishank turbine buckets, with cover plates, mounted on a turbine wheel
  • FIG. 2 is a cross-section, looking in a circumferential direction along lines II-H of FIG. 1, showing the cover plate and means of attachment to the rim;
  • FIG. 3 is a plan view in cross-section, taken along lines IIIIII of FIG. 1, through the cover plates only.
  • FIGS. 4 and 5 are enlarged schematic views, looking in an axial direction, of themeans for locking turbine bucket platforms together, shown when the turbine wheel is atrest and when it is turning, respectively;
  • FIG. 6 is an exploded. perspective View showing the dovetail attachment for the improved cover plate.
  • a portion of a turbine rim 1 is shown which is furnished with a group of circumferentially-spaced axially extending dovetail slots 2 extending around its periphery.
  • a long-shank turbine bucket shown generally as 3, which includes a vane portion 4, an-arcuate bucket platform 5, which forms a portion of the inner boundary wall for the motive fluid flowing through the turbine, and a radially extending bucket shank 6.
  • Shank 6 serves to connect platform 5 to a dovetail base portion 7 which fits in slot 2.
  • cover plates 8 Extending radially between rim 1 and bucket platforms 5 are a number of improved cover plates, shown generally as 8, which likewise have dovetail base porthe cover plates 8 thus fit in the remaining length of the Still another object of the invention is to provide a tions 9 fitting'in dovetail slots 2, 'togetherwith the base portion 7 of the buckets.
  • the cover plates have relatively thin flat plate portions 8a, which serve to block gas flow between shanks 6 and which are tapered toward their radially innermost ends where they are attached to base portions 9. Plate portions 8a are preferablyithinner toward their outermost edges.
  • the tapered plate portions 8a may be provided with arcuate axially-extending flanges 10, which cooperate to form two circumferential, axially extending sealing rings.
  • Cover plates 8 also define notches 11 at their radially outermost edges which support the opposite ends of locking pins 12.
  • the axial length of the dovetail slot 2 in the rotor rim is substantially greater than the axial length'of the bucket dovetail base portion 7f
  • cover plates 15 are divided into two types: inner cover plates 15 and outer cover plates 16, having half-thickness overlapping edges 15a and 16a respectively. Although there will be no tendency for the outer tips of the cover plates to move away from the buckets, they are nevertheless arranged to prevent this possibility. Inner cover plates 15 are not allowed to move axially away from the buckets because of the overlapping edges 16:; of the outer cover plates. Hence, the radially outer tips of cover plates 15, indicated as 17 in FIGS. 1 and 2, terminate just short ofthe bucket platforms 5, for ease of insertion.
  • Grooves 5a are formed of ample size to allow ease of insertion of the outer cover plates 16, and clearances provided so that the outer cover plates 16 do not actually touch or load the bucket platform 5.
  • FIGS. 2, 4 and 5 together will indicate the manner of operation of locking pin 12.
  • the pin is cylindrical and is notched at its ends to provide semi-circular extensions 12a which fit in notches 11in the inner and outer bucket cover plates.
  • the pins When the wheel is stationary, as in FIG. 4, the pins merely rest in grooves 11, but when the wheel is rotating, the pins assume the position shown in FIG. 5.
  • the force exerted by centrifugal action is very great and serves to center the pin between adjacent bucket platforms 5 and effectively lock them together so there is no relative movement between buckets. This is not a clamping device, but actually serves to clamp the bucket platforms firmly together.
  • FIG. 6 shows the method of assembly of the cover plate into the slot 2. It will be observed that the rim 1 of the turbine wheel is provided with an axial projection 1a and an undercut groove 1b, which correspond to axial projection Sa and undercut groove 9b on the cover plate base 9.
  • the base portion 7 of the turbine bucket 3 is centered in slot 2 and then the base portions of the cover plates are inserted from either side of the wheel.
  • Grooves 1b and 915 on the wheel and cover plate respectively are aligned and the retaining strip 13 (see FIGS. 1 and 2) is then inserted radially outward to fit in the aligned grooves, at the same time aligning its holes with those in the cover plate base.
  • pins 14 are'inserted and secured in place. It will be apparent that strip 13 then prevents relative axial movement between rim extensions 1a and cover plate base extensions 9a. Therefore, both buckets and cover plates are locked to the rim 1 and can move neither radially nor axially.
  • the arrangement and construction of the cover plate 8 is such that it presents a moment-free'loading on its dovetail base portion 9.
  • Reference to FIG. 2 of the drawing will show that a radial plane w passing through the axial center of the dovetail base portion 9 represents a line along which the base 9 will be loaded in tension with no bending moments. In other words, if the moments of the cross-sectional area taken from line 19 have a sum of zero, then there will be no bending moments imposed on dovetail base 9 to add to its tensile loading.
  • the metal in the cover plate proper is so distributed and arranged on either side of line 19 that the bending moments in opposite axial directions are balanced.
  • the bulk of the tapered plate portion 8a is balanced by the extending sealing flanges it which have a much greater effect in bending than the plate portion 801, since they extend farther in an axial direction.
  • the axial ex tension 9a of the base portion 9 has a negligible effect, since it carries only its own weight.
  • a dovetail arrangement isone of the most efiicient turbine bucket attachments known, for such a part which has to be removable.
  • the theories and design of the contours of the dovetail slot and mating dovetail portion to fit in that slot have reached a high degree of perfection.
  • the improved cover plate by virtue of being retained inplace on the rim by a dovetail base, permits an extremely light-weight cover plate.
  • the cover plate imposes its own uniform tensile force on the rotor rim without imposing any bending moments thereon.
  • cover plate shown by virtue of distributing the metal about the center of the dovetail base portions 9, exerts a pure radial force on the rim and has no tendency to bend inward or outward under the action of centrifugal force.
  • the cover plate shown neither loads the turbine bucket (which, in turn, would increase the local loading on a portion of the bucket base portion), nor'does it-attach to the bucket or turbine rim by means of lugs or hooks (which create undesirable bending moments and/ or local increased stresses).
  • a cover plate for a long shank turbine bucket comprising:
  • a cover plate for a long shank turbine bucket comprising:
  • a fiat plate portion tapering in front elevation and including at least one arcuate flange extending normal to the plate across its width, and a dovetail base attached to the smaller radially inner end of said plate defining dovetail grooves extending in the direction of the plate thickness, said plate portion The and flangebeing disposed with respect to a plane passing through the center of the base portion transverse to said grooves so that bending moments caused by centrifugal forces when the plate is attached to extend radially outward from a turbine rotor rim by said dovetail base portion will cancel, whereby the flat plate portion is substantially balanced by the flange.
  • a turbine having a rim defining circumferentially spaced, axially extending dovetail slots, a plurality of long shank turbine buckets having dovetail base portions disposed in said slots, said bucket base portions having axial lengths less than those of said dovetail slots, a plurality of cover plates disposed at opposite sides of the bucket shanks, each plate having radially extending flat plate portions tapering in front elevation and disposed adjacent one another so as to block the spaces betweenbucket shanks, each plate portion having a dovetail base portion disposed in a dovetail slot adjacent a bucket base portion, and means preventing relative axial movement between the cover plate base portions and the turbine wheel rim, whereby the cover plates and turbine buckets are individually supported by their respective dovetail base portions.
  • a turbine wheel having a rim defining circumferentially spaced, axially extending dovetail slots
  • a plurality of turbine buckets having dovetail base portions disposed in said slots
  • the buckets also having arcuate platform portions radially spaced from said dovetail base portions and connected thereto by relatively slender shanks
  • a plurality of cover plates disposed at opposite sides of the bucket shanks, each plate having a radially extending flat plate portion tapering in front elevation and having opposite radial edges defining flanges overlapping portions of similar adjacent cover plates
  • each of said cover plates also having attached to the smaller radially inner end thereof a dovetail base portion disposed in a dovetail slot adjacent a bucket base portion, the flat plate portions of said cover portions and connected thereto by relatively slender shanks, a plurality of cover plates disposed at opposite sides of the bucket shanks, each plate including a dovetail base portion disposed in one of said dovetail slots,
  • cover plate base portions and said rim include axially extending projections defining aligned radially undercut grooves, arcuate retaining strips disposed in said grooves to prevent relative axialmovement between cover plates and turbine rim, and means fastening said retaining strips 7 in said grooves, whereby both cover plates and turbine buckets are held in saiddovetail slots against radial and axial disengagement.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US209099A 1962-07-11 1962-07-11 Cover plate assembly for sealing spaces between turbine buckets Expired - Lifetime US3137478A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
NL295165D NL295165A (ko) 1962-07-11
US209099A US3137478A (en) 1962-07-11 1962-07-11 Cover plate assembly for sealing spaces between turbine buckets
GB24670/63A GB1012066A (en) 1962-07-11 1963-06-20 Improvements in cover plate assembly for sealing spaces between turbine blades
DEG38030A DE1212108B (de) 1962-07-11 1963-06-26 Einkraenziges Axial-Stroemungsmaschinen-Laufrad
CH862063A CH403402A (de) 1962-07-11 1963-07-09 Schaufelrad
SE7610/63A SE304417B (ko) 1962-07-11 1963-07-09
FR941096A FR1362926A (fr) 1962-07-11 1963-07-11 Plaque de recouvrement pour assurer l'obturation des intervalles entre des aubes de turbine
NL63295165A NL141273B (nl) 1962-07-11 1963-07-11 Van schoepen voorziene rotor, in het bijzonder een turbinewiel.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US209099A US3137478A (en) 1962-07-11 1962-07-11 Cover plate assembly for sealing spaces between turbine buckets

Publications (1)

Publication Number Publication Date
US3137478A true US3137478A (en) 1964-06-16

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Family Applications (1)

Application Number Title Priority Date Filing Date
US209099A Expired - Lifetime US3137478A (en) 1962-07-11 1962-07-11 Cover plate assembly for sealing spaces between turbine buckets

Country Status (6)

Country Link
US (1) US3137478A (ko)
CH (1) CH403402A (ko)
DE (1) DE1212108B (ko)
GB (1) GB1012066A (ko)
NL (2) NL141273B (ko)
SE (1) SE304417B (ko)

Cited By (50)

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Publication number Priority date Publication date Assignee Title
US3508844A (en) * 1968-07-25 1970-04-28 United Aircraft Corp Blade lock
US3656865A (en) * 1970-07-21 1972-04-18 Gen Motors Corp Rotor blade retainer
DE2258618A1 (de) * 1971-12-06 1973-06-07 Gen Electric Bolzenloser blatt- und dichtungshalter
US3807898A (en) * 1970-03-14 1974-04-30 Secr Defence Bladed rotor assemblies
US3814539A (en) * 1972-10-04 1974-06-04 Gen Electric Rotor sealing arrangement for an axial flow fluid turbine
US3936222A (en) * 1974-03-28 1976-02-03 United Technologies Corporation Gas turbine construction
US4019833A (en) * 1974-11-06 1977-04-26 Rolls-Royce (1971) Limited Means for retaining blades to a disc or like structure
US4033705A (en) * 1976-04-26 1977-07-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blade retainer assembly
US4088421A (en) * 1976-09-30 1978-05-09 General Electric Company Coverplate damping arrangement
US4094615A (en) * 1976-12-27 1978-06-13 Electric Power Research Institute, Inc. Blade attachment structure for gas turbine rotor
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
US4343594A (en) * 1979-03-10 1982-08-10 Rolls-Royce Limited Bladed rotor for a gas turbine engine
US4422827A (en) * 1982-02-18 1983-12-27 United Technologies Corporation Blade root seal
EP0169801A1 (en) * 1984-07-23 1986-01-29 United Technologies Corporation Turbine side plate assembly
US4659285A (en) * 1984-07-23 1987-04-21 United Technologies Corporation Turbine cover-seal assembly
EP0286227A2 (en) * 1987-03-06 1988-10-12 ROLLS-ROYCE plc Turbo machine rotor assembly
US5339619A (en) * 1992-08-31 1994-08-23 United Technologies Corporation Active cooling of turbine rotor assembly
US5486095A (en) * 1994-12-08 1996-01-23 General Electric Company Split disk blade support
EP1081337A2 (en) * 1999-08-31 2001-03-07 General Electric Company Cover plates for turbomachine blades
JP2001182502A (ja) * 1999-12-20 2001-07-06 General Electric Co <Ge> 回転機械動翼の保持装置及び保持方法
EP1284339A1 (de) * 2001-08-14 2003-02-19 Siemens Aktiengesellschaft Abdeckringsystem für Schaufelscheiben von Gasturbinen
US6533550B1 (en) 2001-10-23 2003-03-18 Pratt & Whitney Canada Corp. Blade retention
US20050123405A1 (en) * 2003-12-05 2005-06-09 Honda Motor Co., Ltd. Sealing arrangement for an axial turbine wheel
US20060056975A1 (en) * 2004-09-14 2006-03-16 Honkomp Mark S Methods and apparatus for assembling gas turbine engine rotor assemblies
US20070217904A1 (en) * 2006-03-14 2007-09-20 Dixon Jeffrey A Turbine engine cooling
US20080044284A1 (en) * 2006-08-16 2008-02-21 United Technologies Corporation Segmented fluid seal assembly
US20100215501A1 (en) * 2009-02-25 2010-08-26 General Electric Company Apparatus for bucket cover plate retention
US20100232939A1 (en) * 2009-03-12 2010-09-16 General Electric Company Machine Seal Assembly
US20100232938A1 (en) * 2009-03-12 2010-09-16 General Electric Company Gas Turbine Having Seal Assembly with Coverplate and Seal
US20100329872A1 (en) * 2009-06-30 2010-12-30 Donald Joseph Kasperski Method and apparatus for assembling rotating machines
US20110014050A1 (en) * 2007-10-25 2011-01-20 Peter Lake Turbine blade assembly and seal strip
US20110176923A1 (en) * 2010-01-19 2011-07-21 General Electric Company Seal plate and bucket retention pin assembly
US20120045337A1 (en) * 2010-08-20 2012-02-23 Michael James Fedor Turbine bucket assembly and methods for assembling same
US8128371B2 (en) 2007-02-15 2012-03-06 General Electric Company Method and apparatus to facilitate increasing turbine rotor efficiency
US20130052020A1 (en) * 2011-08-23 2013-02-28 General Electric Company Coupled blade platforms and methods of sealing
WO2013037483A1 (de) * 2011-09-12 2013-03-21 Rolls-Royce Deutschland Ltd & Co Kg Sicherungssegment zur schwingungsdämpfung von turbinenlaufschaufeln und rotorvorrichtung
EP2644832A1 (en) * 2012-03-29 2013-10-02 General Electric Company Near-flow-path seal isolation dovetail of a turbine bucket
US20130256996A1 (en) * 2012-03-28 2013-10-03 General Electric Company Shiplap plate seal
CN103485832A (zh) * 2012-06-12 2014-01-01 通用电气公司 叶片附连组件
US20170306771A1 (en) * 2016-04-20 2017-10-26 Rolls-Royce Deutschland Ltd & Co Kg Rotor with overhang at blades for a locking element
US10145249B2 (en) 2016-02-23 2018-12-04 Mechanical Dynamics & Analysis Llc Turbine bucket lockwire anti-rotation device for gas turbine engine
US10196916B2 (en) 2016-04-08 2019-02-05 Siemens Aktiengesellschaft Rotor disk having an end-side sealing element
WO2019040171A1 (en) * 2017-08-25 2019-02-28 Siemens Aktiengesellschaft PLATE ASSEMBLY
EP3511524A1 (de) * 2018-01-10 2019-07-17 Siemens Aktiengesellschaft Rotor mit in schaufelhaltenuten befestigten dichtelementen
US10494934B2 (en) 2017-02-14 2019-12-03 General Electric Company Turbine blades having shank features
WO2020023005A1 (en) * 2018-07-23 2020-01-30 Siemens Aktiengesellschaft Cover plate with flow inducer and method for cooling turbine blades
WO2020023007A1 (en) * 2018-07-23 2020-01-30 Siemens Aktiengesellschaft Cover plate with flow inducer and method for cooling turbine blades
US10683765B2 (en) 2017-02-14 2020-06-16 General Electric Company Turbine blades having shank features and methods of fabricating the same
US11319823B2 (en) * 2018-02-02 2022-05-03 Siemens Energy Global GmbH & Co. KG Rotor with sealing element and ring seal
US20230160313A1 (en) * 2020-04-07 2023-05-25 Safran Aircraft Engines Turbine rotor for a turbomachine and method for mounting the rotor

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US4192633A (en) * 1977-12-28 1980-03-11 General Electric Company Counterweighted blade damper
GB2307520B (en) * 1995-11-14 1999-07-07 Rolls Royce Plc A gas turbine engine
JP5675674B2 (ja) 2012-02-29 2015-02-25 三菱重工業株式会社 タービン動翼の抜け止め構造およびこれを備えた回転機械
DE102016208759A1 (de) * 2016-05-20 2017-11-23 Siemens Aktiengesellschaft Rotorscheibe mit stirnseitigem Dichtelement
EP3438410B1 (en) 2017-08-01 2021-09-29 General Electric Company Sealing system for a rotary machine

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US3037741A (en) * 1958-12-29 1962-06-05 Gen Electric Damping turbine buckets
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US2755063A (en) * 1950-11-14 1956-07-17 Rolls Royce Rotor constructions for gas-turbine engines
US2920865A (en) * 1952-10-31 1960-01-12 Rolls Royce Bladed stator or rotor constructions with means to supply a fluid internally of the blades
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US2998959A (en) * 1955-09-29 1961-09-05 Rolls Royce Bladed rotor of axial-flow fluid machine with means to retain blades in position on rotor
US2988325A (en) * 1957-07-18 1961-06-13 Rolls Royce Rotary fluid machine with means supplying fluid to rotor blade passages
US2999668A (en) * 1958-08-28 1961-09-12 Curtiss Wright Corp Self-balanced rotor blade
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Cited By (80)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3508844A (en) * 1968-07-25 1970-04-28 United Aircraft Corp Blade lock
US3807898A (en) * 1970-03-14 1974-04-30 Secr Defence Bladed rotor assemblies
US3656865A (en) * 1970-07-21 1972-04-18 Gen Motors Corp Rotor blade retainer
DE2258618A1 (de) * 1971-12-06 1973-06-07 Gen Electric Bolzenloser blatt- und dichtungshalter
US3814539A (en) * 1972-10-04 1974-06-04 Gen Electric Rotor sealing arrangement for an axial flow fluid turbine
US3936222A (en) * 1974-03-28 1976-02-03 United Technologies Corporation Gas turbine construction
US4019833A (en) * 1974-11-06 1977-04-26 Rolls-Royce (1971) Limited Means for retaining blades to a disc or like structure
US4033705A (en) * 1976-04-26 1977-07-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blade retainer assembly
US4088421A (en) * 1976-09-30 1978-05-09 General Electric Company Coverplate damping arrangement
US4094615A (en) * 1976-12-27 1978-06-13 Electric Power Research Institute, Inc. Blade attachment structure for gas turbine rotor
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
US4343594A (en) * 1979-03-10 1982-08-10 Rolls-Royce Limited Bladed rotor for a gas turbine engine
US4422827A (en) * 1982-02-18 1983-12-27 United Technologies Corporation Blade root seal
EP0169801A1 (en) * 1984-07-23 1986-01-29 United Technologies Corporation Turbine side plate assembly
US4659285A (en) * 1984-07-23 1987-04-21 United Technologies Corporation Turbine cover-seal assembly
US4659289A (en) * 1984-07-23 1987-04-21 United Technologies Corporation Turbine side plate assembly
EP0286227A2 (en) * 1987-03-06 1988-10-12 ROLLS-ROYCE plc Turbo machine rotor assembly
EP0286227A3 (en) * 1987-03-06 1989-09-20 Rolls-Royce Plc Turbo machine rotor assembly
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Also Published As

Publication number Publication date
CH403402A (de) 1965-11-30
SE304417B (ko) 1968-09-23
NL295165A (ko)
NL141273B (nl) 1974-02-15
GB1012066A (en) 1965-12-08
DE1212108B (de) 1966-03-10

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