EP0222262A1 - Abdichtungseinrichtung für Turbopumpe - Google Patents

Abdichtungseinrichtung für Turbopumpe Download PDF

Info

Publication number
EP0222262A1
EP0222262A1 EP86115043A EP86115043A EP0222262A1 EP 0222262 A1 EP0222262 A1 EP 0222262A1 EP 86115043 A EP86115043 A EP 86115043A EP 86115043 A EP86115043 A EP 86115043A EP 0222262 A1 EP0222262 A1 EP 0222262A1
Authority
EP
European Patent Office
Prior art keywords
ring
turbine
contact
shell
housing
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.)
Granted
Application number
EP86115043A
Other languages
English (en)
French (fr)
Other versions
EP0222262B1 (de
Inventor
Michel Villeneuve
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.)
EG&G Sealol
EG&G Sealol Inc
Original Assignee
EG&G Sealol
EG&G Sealol Inc
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 EG&G Sealol, EG&G Sealol Inc filed Critical EG&G Sealol
Publication of EP0222262A1 publication Critical patent/EP0222262A1/de
Application granted granted Critical
Publication of EP0222262B1 publication Critical patent/EP0222262B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/10—Shaft sealings
    • F04D29/12—Shaft sealings using sealing-rings
    • F04D29/126—Shaft sealings using sealing-rings especially adapted for liquid pumps
    • F04D29/128—Shaft sealings using sealing-rings especially adapted for liquid pumps with special means for adducting cooling or sealing fluid

Definitions

  • the present invention relates to a turbopump sealing device, more particularly intended to equip the liquid propellant supply assemblies of rocket engines.
  • the sealing means must, for safety reasons, perfectly isolate the propellants, particularly hydrogen, from the turbine compartment.
  • the sealing means must allow the evacuation of the hydrogen passing through the bearings towards the turbine compartment and it must moreover, in certain lubrication systems, fix the flow of hydrogen at a predetermined value necessary for the proper functioning of the bearings.
  • the sealing means currently used are of several types: - labyrinths - contact face seals - retractable face seals - floating rings - segmented joints.
  • the device according to the present invention implements some of the above elementary means, in a new arrangement making it possible to obtain higher performance compared to the existing combinations, in particular: - no possibility of hydrogen leaking to the turbine during cooling, - reduced consumption of pressurization gas, - control of hydrogen flow to the turbine, - longer service life, - reduced overall dimensions and mass, - greater reliability.
  • the sealing device is mounted in a housing concentric with the rotary shaft between the turbine and the pump itself, said housing defining a cavity for an under gas. pressure, delimited on the side of the turbine by a support ring which is integral with it, in contact with a first floating ring immobilized in rotation and, on the side of the pump, by an attached shell of which one face is in contact with a second floating ring immobilized in rotation, itself bearing on a friction ring secured to the shaft, said rings being mounted on a sleeve concentric with said shaft, the shell being further connected to the cavity by a bellows.
  • a turbine 1 is mounted for rotation on a shaft 2 of longitudinal axis LL driving a pump (not shown) and comprising a bearing such as a ball bearing 3.
  • the sealing device comprises a housing 4 included in a general casing 5.
  • the housing 4 defines a cavity C for a pressurizing gas through a conduit D, as will be explained below, itself delimited according to the following arrangement: - on the side of the turbine 1 by a support ring 6 held in the housing, for example by a nut 7, on which a first floating ring 8 is supported with biasing for example by means of a spring 9, said ring 8 consisting of a carbon ring clamped in a metallic hoop immobilized in rotation by engagement of lugs 10 of the hoop in corresponding housings of the housing; - on the side of the bearing 3 of the pump, by an attached shell 11 in which is disposed a second floating ring 12 of the same type as the previous one tooth and, similarly, immobilized in rotation by engagement of pins 13 of its
  • a vibration damper 18 is interposed between the shell 11 and its housing of the housing 4, in order to prevent any amplification of the vibrations generated during operation.
  • the entire device, that is to say the housing 4, is fixed to the general casing 5 by any suitable means, for example stud-nut assemblies 19, a static seal 20 ensuring the seal with respect to the casing .
  • the second floating ring 12 being intended to be able to present a play in the longitudinal direction and to be followed along the contact face 14 by the shell 11, as will be better explained below, the latter is made integral with the housing by the through a metal bellows 21 guaranteeing the continuity of the enclosure C and preventing any passage of fluid.
  • the bellows 21 also provides, by its stiffness and precompression during assembly, an initial force of shell / floating ring 12 / friction ring 16 contact.
  • the cavity C is pressurized, in the usual way, by gaseous helium (GHe), at a pressure P c such that the force tending to bring the ring on the bearing side 12 into contact with its friction ring 16 is greater than the force tending to separate it:
  • FIG. 2 also shows the diameters ⁇ 20 of the outer edge of the surface 14 and ⁇ 4 of the inner edge of the surface 15.
  • the ring 8 limits the consumption of pressurization gas (flow rate leakage Q He towards the turbine cavity B).
  • the turbine 2 is rotated until it reaches full operating speed, the turbine pressure P B increases from partial vacuum (in the case of an engine with upper stages of launchers) or normal atmospheric pressure (in the case of 'a first stage) as well as the bearing pressure.
  • the bellows 21 is compressed and the shell 11 bears on the housing, leaving a clearance J between ring and support ring.
  • the sealing device then behaves like a system with two rings in series, the pressure P c being established at a value between P A and P B.
  • pressurizing gas is particularly critical and must be reduced as much as possible. mum for the following reasons: - economical: soil consumption - onboard weight reduction: flight consumption (after ground / flight pressurization switching)
  • a segmented ring 22 (fig. 5) which ensures contact both on the support ring 6 and on the socket 17 during cooling, the order of magnitude the leakage then being ten times lower than that obtained with the ring.
  • the segmented ring 22 is biased in contact with the support ring 6 by a spring 23.
  • this segmented ring 22 In operation, this segmented ring 22 must be cooled. It must therefore have a hydrodynamic effect so that the segments take off from the sleeve under the action of rotation, thus providing a clearance between ring and sleeve which allows a flow of hydrogen. The absence of contact during operation reduces the power absorbed and allows cooling.
  • the reduction in consumption can also be obtained by using a second ring in series with the first (8).
  • one or two labyrinths 24, 25 can be added downstream of the support and friction rings, 6 and 16 which limit the flow of hydrogen during operation in the event of failure of the rings.
  • the loss of pressurization is also to be considered as a particularly critical failure in the case of an upper stage of a launcher.
EP86115043A 1985-11-08 1986-10-29 Abdichtungseinrichtung für Turbopumpe Expired - Lifetime EP0222262B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8516595A FR2589955B1 (fr) 1985-11-08 1985-11-08 Dispositif d'etancheite de turbopompe
FR8516595 1985-11-08

Publications (2)

Publication Number Publication Date
EP0222262A1 true EP0222262A1 (de) 1987-05-20
EP0222262B1 EP0222262B1 (de) 1990-07-18

Family

ID=9324653

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86115043A Expired - Lifetime EP0222262B1 (de) 1985-11-08 1986-10-29 Abdichtungseinrichtung für Turbopumpe

Country Status (5)

Country Link
US (1) US4744721A (de)
EP (1) EP0222262B1 (de)
JP (1) JPS62182499A (de)
DE (1) DE3672750D1 (de)
FR (1) FR2589955B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3005687A1 (fr) * 2013-05-20 2014-11-21 Snecma Turbopompe avec systeme anti-vibrations

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8422952D0 (en) * 1984-09-11 1984-10-17 Hunt J Performance wing
US6311983B1 (en) * 1989-09-26 2001-11-06 The Boeing Company Combination static lift-off face contact seal and floating ring shaft seal
JPH0462391U (de) * 1990-10-02 1992-05-28
US5567132A (en) * 1994-12-06 1996-10-22 Endura Pumps International, Inc. Seal for pump having an internal gas pump
JP3710702B2 (ja) * 2000-11-14 2005-10-26 イーグル工業株式会社 タンデムシール
US6505834B1 (en) * 2001-11-02 2003-01-14 General Electric Company Pressure actuated brush seal
JP4530132B2 (ja) * 2004-01-22 2010-08-25 株式会社ジェイテクト 電動ポンプ
WO2006137305A1 (ja) * 2005-06-20 2006-12-28 Eagle Industry Co., Ltd. メカニカルシール装置
US7470066B2 (en) * 2006-03-22 2008-12-30 Gm Global Technology Operations, Inc. Pump bearing assembly with seal
JP2009174376A (ja) * 2008-01-23 2009-08-06 Valeo Thermal Systems Japan Corp 圧縮機の軸封構造
FR2964425B1 (fr) * 2010-09-03 2014-02-14 Snecma Turbopompe, en particulier pour l'alimentation de moteurs de fusee
US8845282B2 (en) * 2011-09-28 2014-09-30 United Technologies Corporation Seal plate with cooling passage
WO2014061543A1 (ja) * 2012-10-19 2014-04-24 イーグルブルグマンジャパン株式会社 ベローズシール
US20140265151A1 (en) * 2013-03-15 2014-09-18 Stein Seal Company Circumferential Seal with Ceramic Runner
US9611846B2 (en) * 2014-12-31 2017-04-04 Smith International, Inc. Flow restrictor for a mud motor
DE102016200821B3 (de) * 2016-01-21 2017-05-11 Eagleburgmann Germany Gmbh & Co. Kg Gleitringdichtungsanordnung mit rückseitiger Abdichtung
CN109196255B (zh) * 2016-05-25 2020-06-05 苏尔寿管理有限公司 双重机械密封件、其主固定密封环和离心泵中的泵壳体
CN107939722B (zh) * 2017-11-30 2024-02-09 北京航天动力研究所 一种氢氧发动机涡轮泵用弹簧加载自动脱开式动密封装置
US11054039B2 (en) * 2018-08-31 2021-07-06 Rolls-Royce Corporation Seal runner support
US20200248814A1 (en) * 2019-02-01 2020-08-06 Rolls-Royce Corporation Seal assembly with spring retainer runner mount assembly
US10935142B2 (en) * 2019-02-01 2021-03-02 Rolls-Royce Corporation Mounting assembly for a ceramic seal runner
CN112324591B (zh) * 2020-09-27 2022-01-04 蓝箭航天技术有限公司 一种火箭发动机用低温高转速浮动环密封试验装置
CN112145471B (zh) * 2020-10-22 2022-05-17 航天科工火箭技术有限公司 一种气体脱开式组合动密封装置
CN112431788B (zh) * 2020-10-29 2022-04-22 北京航天动力研究所 一种高速低泄漏液封轮浮动环组合式密封装置
CN112728087B (zh) * 2021-01-07 2023-03-24 湖北航天技术研究院总体设计所 一种用于液体火箭发动机的轴封装置
CN113090575B (zh) * 2021-05-12 2022-07-19 西安航天动力研究所 一种双浮动环密封吹除隔离装置及涡轮泵
US11466584B1 (en) 2021-07-29 2022-10-11 Rolls-Royce Corporation Ceramic runner seal assembly with compliant holder
CN115182829B (zh) * 2022-07-15 2023-05-12 哈尔滨工业大学 一种大压差、高转速浮动环密封测试试验台

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB784708A (en) * 1954-02-23 1957-10-16 James Walker And Company Ltd A mechanical gland seal for rotor shafts of vane and other rotary pumps
US2882075A (en) * 1956-01-31 1959-04-14 Thompson Prod Inc Pump seal
FR1303790A (fr) * 1961-10-13 1962-09-14 Worthington Corp Joint mécanique d'étanchéité à fuite réglée
FR2000565A1 (de) * 1968-01-22 1969-09-12 Borg Warner
US3675933A (en) * 1970-09-03 1972-07-11 Crane Packing Co Seal with installed space parts

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2215034A (en) * 1940-04-12 1940-09-17 James C Gorman Shaft sealing means
US2322867A (en) * 1941-01-10 1943-06-29 Rotary Seal Company Seal
US2575549A (en) * 1948-10-12 1951-11-20 Jabsco Pump Co Rotary shaft seal
US3260530A (en) * 1961-03-27 1966-07-12 Central Res Lab Inc Rotary mechanical seal
US3977685A (en) * 1974-11-05 1976-08-31 Eg&G, Inc. Rotating bellows seal
US4294454A (en) * 1979-02-05 1981-10-13 Cannings John A Rotary seal unit
US4377290A (en) * 1982-03-22 1983-03-22 John Crane-Houdaille, Inc. Symmetrical seal package for multiple face seals
DE3343685A1 (de) * 1983-12-02 1985-06-13 Abel Gmbh & Co Pumpen Und Maschinenbau, 4300 Essen Kreiselpumpe, insbesondere fuer die foerderung von foerdergut in der lebensmittelindustrie

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB784708A (en) * 1954-02-23 1957-10-16 James Walker And Company Ltd A mechanical gland seal for rotor shafts of vane and other rotary pumps
US2882075A (en) * 1956-01-31 1959-04-14 Thompson Prod Inc Pump seal
FR1303790A (fr) * 1961-10-13 1962-09-14 Worthington Corp Joint mécanique d'étanchéité à fuite réglée
FR2000565A1 (de) * 1968-01-22 1969-09-12 Borg Warner
US3675933A (en) * 1970-09-03 1972-07-11 Crane Packing Co Seal with installed space parts

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3005687A1 (fr) * 2013-05-20 2014-11-21 Snecma Turbopompe avec systeme anti-vibrations
WO2014188109A1 (fr) * 2013-05-20 2014-11-27 Snecma Turbopompe avec systeme anti-vibrations
US10190592B2 (en) 2013-05-20 2019-01-29 Arianegroup Sas Turbopump with anti-vibration system

Also Published As

Publication number Publication date
FR2589955B1 (fr) 1989-12-08
EP0222262B1 (de) 1990-07-18
JPS62182499A (ja) 1987-08-10
FR2589955A1 (fr) 1987-05-15
DE3672750D1 (de) 1990-08-23
US4744721A (en) 1988-05-17

Similar Documents

Publication Publication Date Title
EP0222262B1 (de) Abdichtungseinrichtung für Turbopumpe
EP2870323B1 (de) Dichtungsvorrichtung für das lager einer turbomaschine mit zwei elastischen dichtungen
EP0967424B1 (de) Turbomachinenvorrichtung mit einer Dichtung
FR2613791A1 (fr) Palier magnetique radial a atterrisseur de secours et application a une turbomachine a suspension magnetique active
EP0789133A1 (de) Labyrinthträgerscheibe mit einer eingebauten Versteifung für Turbomaschinenrotor
FR2914009A1 (fr) Joints retractables actifs pour turbomachines
FR2929325A1 (fr) Dispositif et procede d'equilibrage de pression dans une enceinte palier de turboreacteur
EP2864676A1 (de) Abdichtungsvorrichtung mit passiver abschaltung für ein system aus wellendichtungen einer primären motorisierten pumpeneinheit
EP0566478A1 (de) Hochdruckdampfturbinengehäuse
FR3005099A1 (fr) Structure de turbomachine comportant une bague de ventilation
FR2595430A1 (fr) Dispositif d'etancheite pour machine a fluide rotative
EP0018892B1 (de) Dichtungsvorrichtung zwischen zwei Teilen einer Turbomaschine
EP1055848B1 (de) Dichtungsanordnung mit Auftrieb für Turbomaschinenlagergehäuse
FR3021067A1 (fr) Circuit de circulation d'air a travers une enceinte palier
EP1186813B1 (de) Berührungsfreie Axialkohlenstoffdichtung für ein Lagergehäuse
FR2893684A1 (fr) Agencement de paliers de secours pour machine tournante a paliers magnetiques actifs
FR3075252A1 (fr) Ensemble d'etancheite
FR3085408A1 (fr) Perfectionnements aux turbomachines
FR3061750B1 (fr) Butee fixe d'un systeme de butees fixe et tournante destine a supporter une charge axiale.
FR2697598A1 (fr) Dispositif de protection contre l'entrée de particules et de polluants solides.
EP1188972A1 (de) Berührungsfreie Axialkohlenstoffdichtung für ein Lagergehäuse
WO2023099850A1 (fr) Pressurisation d'une enceinte lubrifiée de turbomachine
FR2749348A1 (fr) Dispositif de limitation des risques d'incendie a l'interieur d'une turbomachine
FR3103523A1 (fr) Dispositif d’équilibrage
FR3123376A1 (fr) Turbomachine pour aeronef

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE GB IT

17P Request for examination filed

Effective date: 19870828

17Q First examination report despatched

Effective date: 19880816

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE GB IT

REF Corresponds to:

Ref document number: 3672750

Country of ref document: DE

Date of ref document: 19900823

ITF It: translation for a ep patent filed

Owner name: BARZANO' E ZANARDO ROMA S.P.A.

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
ITTA It: last paid annual fee
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19951016

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19951020

Year of fee payment: 10

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19961029

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 19961029

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19970701

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20051029