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WO2012052740A1 - Dispositif d'étanchéité pour réduire la fuite de fluide dans une turbine - Google Patents

Dispositif d'étanchéité pour réduire la fuite de fluide dans une turbine Download PDF

Info

Publication number
WO2012052740A1
WO2012052740A1 PCT/GB2011/051892 GB2011051892W WO2012052740A1 WO 2012052740 A1 WO2012052740 A1 WO 2012052740A1 GB 2011051892 W GB2011051892 W GB 2011051892W WO 2012052740 A1 WO2012052740 A1 WO 2012052740A1
Authority
WO
WIPO (PCT)
Prior art keywords
fluid
leakage
rotor
stator
sealing device
Prior art date
Application number
PCT/GB2011/051892
Other languages
English (en)
Inventor
Simon Ian Hogg
Original Assignee
University Of Durham
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 University Of Durham filed Critical University Of Durham
Publication of WO2012052740A1 publication Critical patent/WO2012052740A1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/164—Sealings between relatively-moving surfaces the sealing action depending on movements; pressure difference, temperature or presence of leaking fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/40—Sealings between relatively-moving surfaces by means of fluid
    • F16J15/406—Sealings between relatively-moving surfaces by means of fluid by at least one pump
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • F16J15/443—Free-space packings provided with discharge channels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • F16J15/447—Labyrinth packings
    • F16J15/4472—Labyrinth packings with axial path

Definitions

  • the present invention relates to a sealing device for reducing leakage of working fluid in a turbine apparatus, and relates particularly, but not exclusively, to a sealing apparatus for minimising leakage of superheated steam between the rotor and stator of steam turbine power generating apparatus .
  • FIG. 1 shows a known type of turbine arrangement used in a high pressure steam turbine power generator.
  • the turbine arrangement 2 has a stator 4 and a rotor 6 mounted for rotation about an axis in order to drive an electricity generator (not shown) .
  • the rotor 6 and stator 4 are provided with opposed sets of blades 8 such that when superheated steam is introduced through an inlet 10 of the stator 4, the heat energy of the steam is transferred to the turbine blades 8, which in turn causes the rotor 6 to rotate about its axis, and the steam is then exhausted from an outlet 12.
  • a typical labyrinth seal used as a shaft gland seal is shown in Figures 2A to 2C and consists of a rotating aerodynamic seal used to reduce unwanted leakage flow between the rotor and the stator.
  • the seal consists of a series of tight restrictions 18, 20 between the opposing rotor and stator surfaces and are formed by fins 22 on the stationary and sometimes also on the rotating components, with small clearances (typically less than 1mm) between the tips of the fins 22 and the adj cent sealing surface, as shown in Figure 2C.
  • the leakage flow through each restriction forms a j et which expands into the relatively large volume between the sealing fin 22 forming the jet and the next fin 22 downstream.
  • FIGS 3A to 3C Although brush and leaf seals have good sealing performance, present contacting seal technology is found to be insuff ciently durable for routine long term applications in gas and steam turbine environments. It is found that real turbine phenomena such as high velocity impacts from solid particles carried by the fluid flow, or high levels of swirl in the approaching flow (resulting in chaotic fluttering of seal bristles) are known to cause bristles to break off in use, leading to rapid degradation in sealing performance.
  • US 2685429 discloses an arrangement shown in Figures 5A and 5B in which the fluidic sealing jet is provided from a remote pressurised source through inlet port 120 and inclined fluidic jet hole 115. This arrangement enables the sealing jet to be supplied at elevated pressure, but increases the cost and complexity of the turbine apparatus.
  • a sealing device for reducing fluid leakage between a rotor and a stator of a turbine apparatus in which at least one rotor is adapted to rotate about a respective axis relative to a stator, the sealing device comprising: - at least one fluid engaging member adapted to engage fluid having a respective first pressure adjacent at least one inlet to a respective leakage region between a said rotor and said stator;
  • At least one fluid outlet member adapted to direct fluid into said leakage region so as to reduce the rate of leakage of fluid through said leakage region
  • At least one conduit connecting at least one said fluid engaging member to at least one said fluid outlet member, wherein at least one said fluid engaging member is adapted to engage fluid such that kinetic energy resulting from a swirl component of motion of said fluid causes fluid in the corresponding said conduit to be at a respective second pressure, higher than the respective said first pressure.
  • the present invention is based on the discovery that significantly improved leakage reduction can be achieved at elevated fluidic seal pressures which can be derived from the kinetic energy of flow of working fluid, rather than
  • At least one said fluid engaging member may comprise a respective first tube.
  • At least one said fluid engaging member may comprise a respective concave member.
  • At least one said fluid engaging member may comprise a respective plate.
  • At least one said fluid outlet member may be adapted to produce a jet of fluid.
  • At least one said conduit may comprise fluid reservoir means .
  • This provides the advantage of enabling the second pressure to be significantly higher than the corresponding first pressure.
  • a turbine apparatus comprising :- a stator
  • At least one rotor adapted to rotate about a respective axis relative to said stator
  • At least one sealing device as defined above. At least one said sealing device may be mounted to a respective rotor.
  • At least one said sealing device may be mounted to the stator .
  • At least one said rotor may comprise a plurality of turbine blades, and at least one said sealing device may be adapted to reduce leakage around the radial periphery of said bl des .
  • At least one said sealing device may be adapted to reduce leakage between a shaft of at least one said rotor and the stator.
  • Figure 1 is a schematic cross sectional view of a known steam turbine apparatus
  • Figure 2A is a perspective view of a stationary gland housing of the turbine cylinder of Figure 1 employing known labyrinth seal technology;
  • Figure 2B is a perspective part cross sectional view of part of a gland seal ring of Figure 2A co-operating with a rotor (not shown) to form a labyrinth seal
  • Figure 2C is a schematic cross sectional view (now shown including the rotor) of the labyrinth part of the seal of Figure 2B;
  • Figures 3A to 3C show a known type of brush seal arrangement
  • Figure 4 is a cross sectional schematic view of a first known fluidic seal
  • Figure 5A is a cross sectional view of a second known fluidic seal
  • Figure 5B is an enlarged cross sectional view of part of the seal of Figure 5A;
  • Figure 6 is a schematic cross sectional view of a fluidic seal of a first embodiment of the present invention.
  • Figures 7A and 7B are detailed views of the fluidic seal of Figure 6;
  • Figures 8A to 8C illustrate fluid dynamic modelling of the performance of the seal of Figure 6;
  • Figure 9 is a perspective view, corresponding to Figure 7A, of a second embodiment of the present invention.
  • Figure 10 is a perspective view, corresponding to
  • Figure 7A of a third embodiment of the present invention
  • Figure 11 is a partially cutaway perspective view of a fluidic seal of a fourth embodiment of the present invention.
  • a turbine apparatus 102 has a rotor 104 rotating about a rotation axis 106 relative to a stator 108.
  • the rotor 104 is provided with axially separated sets of rotor blades 110 surrounded by respective shrouds 112, and the stator 108 is provided with stator blades 114 arranged between sets of axially separated rotor blades 110 such that superheated steam entering an inlet (not shown) is directed by the stator blades 114 so as to contact the rotor blades 110 in a direction designed for maximum efficiency of energy transfer.
  • a fluidic seal 116 is provided between a shaft gland 118 on the stator 108 and the rotor shaft 120, and a fluidic seal 122 is provided between the stator 108 and the outer periphery of the shrouds 112 surrounding the rotor blades 110.
  • the fluidic seal 122 has a three fin non-see-through moving blade tip seal formed by a pair of radially extending fins 124, 126 mounted to the stator 108 and an inclined fin 128 mounted to the stator 108 between the radially extending fins 124, 126, and a series of raised lands 130 on the rotor shroud 112.
  • a fluidic sealing apparatus includes a series of circumferentially arranged fluid inlet ports 132 ( Figure 7A) consisting of tubes of generally circular cross section bent through approximately 90° and arranged in a seal inlet region 134 such that a swirl component of fluid flow in the seal inlet region 134 impinges directly onto the inlet openings of the tubes 132.
  • the tubes 132 are connected to a
  • the cross sectional area of the ports 132 supplying the reservoir chamber 136 is significantly larger than the cross sectional area of the fluid jets 138, and the circumferential cross sectional area of the reservoir chamber 136 is also large compared with the total cross sectional area of the fluid jets 138 supplied from it. As a result, fluid
  • velocities within the reservoir chamber 136 are low.
  • the fluid approaching the inlets 132 will be at seal inlet pressure and will have a component of kinetic energy caused by the swirl component of the velocity field in this region.
  • As flow enters an inlet tube 132 and flows along it into the reservoir chamber 136 its velocity is reduced to the low level of the fluid within the reservoir, and as the velocity of the flow reduces, some of the kinetic energy from the swirl is recovered and the pressure of the fluid is
  • Figures 8A to 8C show computational fluid dynamic calculations carried out on a three fin labyrinth seal of Figure 6 having a geometry as shown in Figure 8A, with and without a fluidic jet injected along the upstream surface of the inclined fin 138.
  • the calculations were carried out at two separate boundary conditions. These were set to be representative of turbine stage seal flows in high and low pressure steam turbine environments.
  • the simulations used air as the working fluid.
  • the temperature for the air used in the calculations is chosen to give flow densities that are representative of steam at these turbine conditions.
  • the pressure at the inlet plane for the calculations i.e. position 1 in Figure 8A
  • the pressure at the calculation exit plane position 3 in Figure 8A
  • P 3 95bar.
  • the inlet and exit steam pressures are set to
  • Table 1 Predicted Leakage Flows with and without Fluidic Jets for conditions representative of high pressure steam turbines.
  • Table 2 Predicted Leakage Flows with and without Fluidic Jets for conditions representative of low pressure steam turbines.
  • generating set ⁇ high pressure, intermediate pressure and low pressure turbine cylinders may generate 600 MW of output, and approximately 30% of this output (i.e. 180 MW) is generated by the high pressure turbine cylinder (for example as shown in Figure 1) , if the efficiency of the high pressure turbine is improved by 0.56% this equates to approximately 1 MW of additional power output.
  • the swirl velocity in the tip seal inlet region 134 of a typical steam turbine high pressure stage is usually in the range of 200 m/s to 250 m/s .
  • the density of the steam is also relatively high due to the high pressure level (a typical value of steam density in this region may be 35Kg/m 3 ) . If all of the kinetic energy in the swirl velocity field could be recovered by the system, this would result in reservoir pressures in the region of 5bar to lobar higher than the tip seal inlet pressure, i.e. values of the pressure ratio (PR) in the range 2 to 3.
  • PR pressure ratio
  • Figure 9 shows a further embodiment of the invention applied to a turbine blade tip seal.
  • inlet scoops 232 in the form quarter-spheres are used at the entry to the reservoir 236 instead of the bent tubes shown in Figure 7.
  • the flow in the seal inlet region 334 stagnates (i.e. stops) in the swirl direction as it impinges on the plates 332, and this results in increased pressure in the region of the upstream side of the plate 332 because of recovery of some of the swirl kinetic energy.
  • the ports 340 supplying the fluidic seal reservoir 336 draw fluid from this higher pressure region, and this results in elevated pressure in the reservoir 336.
  • FIG. 6 is shown.
  • the seal 116 is formed by a stationary gland seal ring 450 having a labyrinth consisting of three long fins 452 and a number of shorter fins 454 cooperating with four raised lands 456 on the rotor, with the same small clearance between stationary and rotating surfaces at all seven of these locations.
  • the first two long fins 452 are inclined radially in the direction of leakage flow, and both of these fins 452 have fluidic jets 458 applied to their upstream surfaces, in a manner similar to the arrangement of Figures 6, 7, 9 and 10.
  • the fluidic jets 458 are supplied through holes through an internal reservoir 460 machined into the stationary gland ring 450, and the reservoir 460 is supplied through ports 462 drilled into the vertical upstream face of the gland seal ring 450.
  • the ports 462 supplying the reservoir 460 are fitted with tubes bent in the opposite direction to the rotating surface of the shaft, so that the swirl energy caused, at least in part, by the rotation of the shaft impinges on the inlet openings of the tubes. In a manner similar to the blade tip seal embodiments described above, this arrangement results in the recovery of some of the kinetic energy from the swirl in the flow in the seal inlet region, resulting in elevated pressures in the
  • reservoir 460 supplying the fluidic jets.
  • the above embodiments have been described by way of example only, and not in any limitative sense, and that various alterations and modifications are possible without departure from the scope of the invention as defined by the appended claims.
  • the embodiments described above use a reservoir between the fluidic jet flow inlet ports and the jets, it will be appreciated by persons skilled in the art that these elements could be directly connected to each other.
  • the fluid jet is applied to the upper surface of an inclined fin, other geometries are possible, for example jets only with no fins, similar to the

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention porte sur un dispositif d'étanchéité (122) destiné à réduire la fuite de fluide entre un rotor (104) et un stator (108) d'une turbine (102). Le dispositif d'étanchéité (122) comprend une série d'orifices d'entrée de fluide (132) qui sont tels qu'une composante tourbillonnante de flux de fluide dans une région d'entrée de joint (134) tombe directement dans les ouvertures d'entrée des orifices d'entrée (132), et une série de jets de fluide (138) projetant du fluide dans une région de fuite de manière à réduire le taux de fuite du fluide à travers la région de fuite. Un conduit (136) relie les orifices d'entrée (132) aux jets (138). L'énergie cinétique résultant d'une composante tourbillonnaire du mouvement du fluide a pour effet que le fluide présent dans la conduite (136) est à une plus haute pression que dans la région d'entrée de joint (134).
PCT/GB2011/051892 2010-10-18 2011-10-05 Dispositif d'étanchéité pour réduire la fuite de fluide dans une turbine WO2012052740A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1017525.5 2010-10-18
GB201017525 2010-10-18

Publications (1)

Publication Number Publication Date
WO2012052740A1 true WO2012052740A1 (fr) 2012-04-26

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2508780A1 (fr) * 2011-04-04 2012-10-10 Rolls-Royce Plc. Joint
WO2014191780A1 (fr) * 2013-05-31 2014-12-04 Cummins Ltd Ensemble joint
CN104896100A (zh) * 2015-05-25 2015-09-09 沈阳航空航天大学 一种降低预旋抑制气流失稳力的反旋流梳齿密封结构
US9359908B2 (en) 2014-07-08 2016-06-07 General Electric Company Film riding seal assembly for turbomachinery
ITUB20160240A1 (it) * 2016-01-20 2017-07-20 Turboden Srl Metodo e dispositivo per ridurre le perdite di trafilamento in una turbina
EP3358142A1 (fr) * 2017-02-02 2018-08-08 General Electric Company Contrôle de fuite à travers d'une virole d'aube de turbines
US10161259B2 (en) 2014-10-28 2018-12-25 General Electric Company Flexible film-riding seal
EP3734019A1 (fr) * 2019-05-01 2020-11-04 Raytheon Technologies Corporation Joint labyrinthe à clapet de retenue passif
CN114207253A (zh) * 2019-08-07 2022-03-18 赛峰直升机发动机公司 用于涡轮发动机的轮部的可移动桨叶

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL80754C (fr) *
US2685429A (en) 1950-01-31 1954-08-03 Gen Electric Dynamic sealing arrangement for turbomachines
JPS5257410A (en) * 1975-11-07 1977-05-11 Hitachi Ltd Leakage sealing mechanism for axial fluid machine
US4178129A (en) * 1977-02-18 1979-12-11 Rolls-Royce Limited Gas turbine engine cooling system
EP0457241A1 (fr) * 1990-05-14 1991-11-21 Gec Alsthom Sa Etage de turbine à action avec pertes secondaires réduites
EP0457240A1 (fr) * 1990-05-14 1991-11-21 Gec Alsthom Sa Etage de turbomachine avec pertes secondaires réduites
EP0623768A1 (fr) * 1993-05-03 1994-11-09 Dresser-Rand Company Joint à labyrinthe
US6000701A (en) * 1997-12-15 1999-12-14 Dresser-Rand Company Labyrinth seal assembly and method
US6264425B1 (en) * 1998-10-05 2001-07-24 Asea Brown Boveri Ag Fluid-flow machine for compressing or expanding a compressible medium
EP1420145A2 (fr) * 2002-11-15 2004-05-19 Rolls-Royce Plc Dispositif d'étanchéité
US20060153673A1 (en) * 2004-11-17 2006-07-13 Volker Guemmer Turbomachine exerting dynamic influence on the flow
US20090297341A1 (en) 2008-06-02 2009-12-03 General Electric Company Fluidic sealing for turbomachinery
US20090324384A1 (en) * 2006-07-26 2009-12-31 Mtu Aero Engines Gmbh Gas turbine having a peripheral ring segment including a recirculation channel

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL80754C (fr) *
US2685429A (en) 1950-01-31 1954-08-03 Gen Electric Dynamic sealing arrangement for turbomachines
JPS5257410A (en) * 1975-11-07 1977-05-11 Hitachi Ltd Leakage sealing mechanism for axial fluid machine
US4178129A (en) * 1977-02-18 1979-12-11 Rolls-Royce Limited Gas turbine engine cooling system
EP0457241A1 (fr) * 1990-05-14 1991-11-21 Gec Alsthom Sa Etage de turbine à action avec pertes secondaires réduites
EP0457240A1 (fr) * 1990-05-14 1991-11-21 Gec Alsthom Sa Etage de turbomachine avec pertes secondaires réduites
EP0623768A1 (fr) * 1993-05-03 1994-11-09 Dresser-Rand Company Joint à labyrinthe
US6000701A (en) * 1997-12-15 1999-12-14 Dresser-Rand Company Labyrinth seal assembly and method
US6264425B1 (en) * 1998-10-05 2001-07-24 Asea Brown Boveri Ag Fluid-flow machine for compressing or expanding a compressible medium
EP1420145A2 (fr) * 2002-11-15 2004-05-19 Rolls-Royce Plc Dispositif d'étanchéité
US20060153673A1 (en) * 2004-11-17 2006-07-13 Volker Guemmer Turbomachine exerting dynamic influence on the flow
US20090324384A1 (en) * 2006-07-26 2009-12-31 Mtu Aero Engines Gmbh Gas turbine having a peripheral ring segment including a recirculation channel
US20090297341A1 (en) 2008-06-02 2009-12-03 General Electric Company Fluidic sealing for turbomachinery

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9039014B2 (en) 2011-04-04 2015-05-26 Rolls-Royce Plc Seal
EP2508780A1 (fr) * 2011-04-04 2012-10-10 Rolls-Royce Plc. Joint
WO2014191780A1 (fr) * 2013-05-31 2014-12-04 Cummins Ltd Ensemble joint
GB2530216A (en) * 2013-05-31 2016-03-16 Cummins Ltd A seal assembly
GB2530216B (en) * 2013-05-31 2016-12-21 Cummins Ltd A seal assembly
US10301959B2 (en) 2013-05-31 2019-05-28 Cummins Ltd. Seal assembly
US9359908B2 (en) 2014-07-08 2016-06-07 General Electric Company Film riding seal assembly for turbomachinery
US10161259B2 (en) 2014-10-28 2018-12-25 General Electric Company Flexible film-riding seal
CN104896100A (zh) * 2015-05-25 2015-09-09 沈阳航空航天大学 一种降低预旋抑制气流失稳力的反旋流梳齿密封结构
WO2017125858A1 (fr) 2016-01-20 2017-07-27 Turboden Spa Procédé et dispositif pour réduire des pertes de fuite dans une turbine
ITUB20160240A1 (it) * 2016-01-20 2017-07-20 Turboden Srl Metodo e dispositivo per ridurre le perdite di trafilamento in una turbina
EP3358142A1 (fr) * 2017-02-02 2018-08-08 General Electric Company Contrôle de fuite à travers d'une virole d'aube de turbines
JP2020505555A (ja) * 2017-02-02 2020-02-20 ゼネラル・エレクトリック・カンパニイ タービンの先端バランススリット
US11092028B2 (en) 2017-02-02 2021-08-17 General Electric Company Tip balance slits for turbines
JP7187464B2 (ja) 2017-02-02 2022-12-12 ゼネラル・エレクトリック・カンパニイ タービンの先端バランススリット
EP3734019A1 (fr) * 2019-05-01 2020-11-04 Raytheon Technologies Corporation Joint labyrinthe à clapet de retenue passif
US11047249B2 (en) 2019-05-01 2021-06-29 Raytheon Technologies Corporation Labyrinth seal with passive check valve
CN114207253A (zh) * 2019-08-07 2022-03-18 赛峰直升机发动机公司 用于涡轮发动机的轮部的可移动桨叶

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