EP0222262B1 - Abdichtungseinrichtung für Turbopumpe - Google Patents

Abdichtungseinrichtung für Turbopumpe Download PDF

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Publication number
EP0222262B1
EP0222262B1 EP86115043A EP86115043A EP0222262B1 EP 0222262 B1 EP0222262 B1 EP 0222262B1 EP 86115043 A EP86115043 A EP 86115043A EP 86115043 A EP86115043 A EP 86115043A EP 0222262 B1 EP0222262 B1 EP 0222262B1
Authority
EP
European Patent Office
Prior art keywords
ring
housing
shell
turbine
contact
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
EP86115043A
Other languages
English (en)
French (fr)
Other versions
EP0222262A1 (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
Original Assignee
EG&G Sealol
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 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

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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 members suitable for sealing essentially comprise, in a housing coaxial with the shaft limited in particular by a fixed support ring, a socket integral with said shaft on which is mounted a stationary ring carried by a support ring, immobilized in rotation, the sleeve being further in contact with a sealing bellows, said rings being able to be subjected to a lubricant introduced under pressure.
  • a device only provides sealing in dynamic regime by solely facial contact of the rings between a stationary side connected to the housing and a rotating side connected to the rotating shaft, excluding the possibility of allowing sealing at rest. and a controlled leak during rotation.
  • 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 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 Pc 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 tending force to separate it: expression in which: ⁇ 1 , ⁇ 3 , 0 5 are respectively the diameters of the cavity, the internal edge of the surface 14 and the external edge of the surface 15; and P A is the pressure of hydrogen at the pump, It should be noted that the diameters 0 2 of the outer edge of the surface 14 and 0 4 of l have also been shown in FIG. interior edge of the surface 15.
  • Ge gaseous helium
  • the ring 8 limits the consumption of pressurization gas (flow rate leakage Q H e 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 Pe.
  • 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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Mechanical Sealing (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Of Bearings (AREA)

Claims (7)

1. Abdichtungseinrichtung einer für Flüssigtreibstoff bestimmten Turbopumpe die zur Gattung gehört in welcher die Turbopumpe in einem zum Drehschaft (2) coaxialen Gehäuse (4) montiert ist auf welcher eine für drehfest schwebende Ringe (8, 12) bestimmte Traghülse (17) befestigt ist, indem das genannte Gehäuse eine für ein Druck schaffendes Gas bestimmte Hohlung (C) umgrenzt, dadurch gekennzeichnet, daß die Hohlung turbinenseitig (1) durch einen zum genannten Gehäuse befestigten Ring (6) auf welchem ein erster schwebender Ring (6) gestützt ist, und pumpenseitig Pumpe (A) durch eine zum genannten Gehäuse angebrachte Schale (11) mit welchem sie mittels eines Balges (21) zwecks Bildung der genannten Hohlung verbunden ist, indem sie selbst drehfest gelagert ist, begrenzt ist, indem die genannte Schale zusätzlich mit einem zweiten schwebenden Ring (12) mit gesteuertem radialen (e) und axialen (j) Spiel in Berührung steht, welcher je nach der Betriebsgestaltung auf der Außenseite (14) der genannten Schale, oder auf der Innenseite (15) eines fest mit dem Schaft gelagerten Reibungsringes (16) sich abstützen kann.
2. Einrichtung nach Anspruch 1, dadurch gekennzeichnet, daß das Gehäuse mit Zwischenschaltung einer feststehenden Dichtung (20) auf einem Kasten (5) festgehalten wird.
3. Einrichtung nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, daß ein Schwingungsdämpfer (18) zwischen der Schale und dem Gehäuse gelagert ist.
4. Einrichtung nach irgendeinem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß der erste turbinenseitige auf der Hülse (17) gelagerte schwebende Ring (8) mit seinem Abstützungsring (6) unter der Belastung einer Feder (9) in Berührung steht.
5. Einrichtung nach irgendeinem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß der erste turbinenseitige Dichtring aus einem Segmentring (22) ausgebildet ist, welcher unter der Belastung einer Feder (23) mit dem Abstützungsring (6) in Kontakt steht.
6. Einrichtung nach irgendeinem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß mindestens die Schale (11) oder der Abstützungsring (6) durch eine Labyrinthdichtung (24, 25) gegenüber der Pumpe (A) abwärts verlängert ist.
7. Einrichtung nach irgendeinem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß das gepumpte Fluid Wasserstoff ist und daß das für das Unterdrucksetzen in der Hohlung (C) verwendete Gas Helium ist.
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
FR8516595 1985-11-08
FR8516595A FR2589955B1 (fr) 1985-11-08 1985-11-08 Dispositif d'etancheite de turbopompe

Publications (2)

Publication Number Publication Date
EP0222262A1 EP0222262A1 (de) 1987-05-20
EP0222262B1 true 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
CN112145471A (zh) * 2020-10-22 2020-12-29 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

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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
CN101198811B (zh) * 2005-06-20 2012-08-22 伊格尔工业股份有限公司 机械密封装置
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
JP6158205B2 (ja) * 2012-10-19 2017-07-05 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
FR3005687B1 (fr) * 2013-05-20 2017-09-15 Snecma Turbopompe avec systeme anti-vibrations
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
EP3464964B1 (de) * 2016-05-25 2019-10-30 Sulzer Management AG Doppelte mechanische dichtung, tragring für einen stationären gleitring dafür und verfahren zum zirkulieren einer barrierenflüssigkeit auf einer doppelten mechanischen dichtung
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
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
US12455010B2 (en) * 2023-10-11 2025-10-28 Schaeffler Technologies AG & Co. KG Seal arrangement

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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
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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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112145471A (zh) * 2020-10-22 2020-12-29 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
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

Also Published As

Publication number Publication date
EP0222262A1 (de) 1987-05-20
US4744721A (en) 1988-05-17
FR2589955B1 (fr) 1989-12-08
JPS62182499A (ja) 1987-08-10
DE3672750D1 (de) 1990-08-23
FR2589955A1 (fr) 1987-05-15

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