CN113623271A - Gas turbine, adjustable guide vane adjusting mechanism and linkage ring limiting device thereof - Google Patents

Gas turbine, adjustable guide vane adjusting mechanism and linkage ring limiting device thereof Download PDF

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Publication number
CN113623271A
CN113623271A CN202010373650.6A CN202010373650A CN113623271A CN 113623271 A CN113623271 A CN 113623271A CN 202010373650 A CN202010373650 A CN 202010373650A CN 113623271 A CN113623271 A CN 113623271A
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China
Prior art keywords
ring
limiting
linkage
link
casing
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CN202010373650.6A
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Chinese (zh)
Inventor
陆晓锋
江奔
宋丹
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AECC Commercial Aircraft Engine Co Ltd
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AECC Commercial Aircraft Engine Co Ltd
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Priority to CN202010373650.6A priority Critical patent/CN113623271A/en
Publication of CN113623271A publication Critical patent/CN113623271A/en
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    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/002—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids by varying geometry within the pumps, e.g. by adjusting vanes
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)

Abstract

One object of the present invention is to provide a link ring position limiter which can maintain a small gap between a position limiting sleeve and a casing under various operating conditions of an engine, thereby improving the reliability of a compressor and the engine. Another object of the present invention is to provide an adjustable guide vane adjusting mechanism, which includes the aforementioned link ring limiting device. It is a further object of the present invention to provide a gas turbine engine comprising the adjustable vane adjustment mechanism described above. To achieve the above object, a link ring limiting device includes a limiting rod, an expansion base, and a limiting arc plate. Wherein, in order to maintain the limit clearance, the thermal expansion coefficient a of the casing material1Coefficient of thermal expansion a with the material of the expansion base2Satisfies the formula: r1Ha1＝L2a2. Wherein R is1The radius of the case at normal temperature, the initial height of the radio and tape player at normal temperature, and the initial length of the radio and tape player at normal temperature.

Description

Gas turbine, adjustable guide vane adjusting mechanism and linkage ring limiting device thereof
Technical Field
The invention relates to a gas turbine, an adjustable guide vane adjusting mechanism and a linkage ring limiting device thereof.
Background
In order to meet the requirement of high efficiency and high margin of an aircraft engine gas compressor, the design of adjustable angles of the first-stage stators is usually adopted to meet the pneumatic performance at different rotating speeds. When the adjustable guide vane is realized through a mechanical structure, the angle control precision of the whole circle of mirror blades is extremely important for the stable and normal work of the compressor. The adjustable guide vane adjusting mechanism of the compressor of the current civil aircraft engine generally comprises a linkage ring and a driving structure thereof, wherein the linkage ring is connected with each guide vane, and the rotation of the linkage ring drives the rotation of a whole circle of guide vanes.
Fig. 1 to 2 show schematic diagrams of a typical adjustable guide vane adjusting mechanism in an existing aircraft engine. The rotating shaft at the upper end of the adjustable guide vane 91 penetrates through square holes of the casing 92 and the rocker arm 94 through a bushing 98 and is fixed by a nut 95. The square hole of the rocker arm 94 is matched with the square shaft on the adjustable guide vane 91, the other end of the rocker arm 94 is provided with a joint bearing 97 and is connected with the linkage half ring 93 through a pin shaft 96, the linkage ring lap joint section 913 is provided with the two linkage half rings 93 into an integral ring structure through bolts 914, and the rocker arm 94 is driven to rotate around the rotating shaft of the adjustable guide vane 91 through the rotation of the linkage integral ring, so that the adjustable guide vane 91 rotates around the rotating shaft of the adjustable guide vane 91, and the angle adjusting function is achieved. Due to the radial clearance between the rocker arm 94 and the half link ring 93, the linkage ring is not in a fully constrained state and is not unique to the concentricity of the casing 92, which may result in inconsistent angles of the adjustable guide vanes 91 at different circumferential positions.
In order to solve the above problems, a link ring limiting device 8 as shown in fig. 3 is usually provided, the link ring limiting device 8 is composed of a limiting rod 81, a bushing 82, a nut 83 and a limiting sleeve 84, and the concentricity of the link half ring 93 and the casing 92 is controlled by controlling a small gap between the limiting sleeve 84 and the casing 92, so as to ensure the consistency of the circumferential angle of the adjustable guide vane 91, but because the casing 92 expands when heated in a working state, in order to prevent the interference and the jamming between the limiting sleeve 84 and the casing 92, the cold gap is usually designed to be very large (0.2-1 mm). However, the inventor finds that in a non-high state, the uniformity of the adjustable guide vanes 91 in the circumferential direction is poor, the compressor margin is reduced, and the reliability of the engine is reduced. Therefore, a new linkage ring limiting device is needed to achieve the purpose that the limiting sleeve and the casing keep a small clearance state under each working condition of the engine, and the reliability of the gas compressor and the engine is improved.
Disclosure of Invention
One object of the present invention is to provide a link ring position limiter which can maintain a small gap between a position limiting sleeve and a casing under various operating conditions of an engine, thereby improving the reliability of a compressor and the engine.
Another object of the present invention is to provide an adjustable guide vane adjusting mechanism, which includes the aforementioned link ring limiting device.
It is a further object of the present invention to provide a gas turbine engine comprising the adjustable vane adjustment mechanism described above.
To achieve the foregoing object, a link ring position limiter includes:
the limiting rod penetrates through the linkage half ring and is provided with a limiting end arranged towards the casing;
the expansion base is arranged on the casing at a position corresponding to the limiting end; and
the limiting arc plate is supported on the expansion base by a retraction mechanism, and a limiting gap is kept between the top surface of the limiting arc plate and the limiting end;
wherein, in order to maintain the limit clearance, the thermal expansion coefficient a of the casing material1Coefficient of thermal expansion a with the expansion base material2Satisfies the following formula:
R1Ha1＝L2a2；
wherein R is1The radius of the case at normal temperature, the initial height of the retraction mechanism at normal temperature and the initial length of the retraction mechanism at normal temperature are shown as H.
In one or more embodiments, the expansion base is made of M152 stainless steel.
In one or more embodiments, the retraction mechanism is an X-shaped leg retraction mechanism.
In one or more embodiments, the circle on which the limiting arc plate is located, the circle on which the casing is located, and the circle on which the linkage half rings are located are concentric.
In one or more embodiments, the expansion base is in intimate contact with the casing.
In one or more embodiments, a limiting sleeve is arranged at one end of the limiting rod after penetrating through the linkage half rings, and the limiting sleeve is provided with the limiting end.
In one or more embodiments, the link ring limiting device is suitable for an environment with a temperature variation between 75 and 375 degrees celsius.
In order to achieve the another purpose, the adjustable guide vane adjusting mechanism comprises a bushing, a rocker arm and a linkage half ring, wherein two ends of the rocker arm are respectively connected with the bushing and the linkage half ring, and the linkage half ring limiting device is arranged between the linkage half ring and a casing.
In one or more embodiments, the linkage half rings are connected to form a complete ring-shaped linkage ring through linkage ring overlapping sections, and the linkage ring limiting devices are arranged in a plurality along the circumferential direction of the linkage ring.
To achieve the aforementioned further object, a gas turbine includes the adjustable vane adjustment mechanism as described above.
The invention has the advantages that when the casing is subjected to thermal expansion, the expansion base is also subjected to thermal expansion, and the thermal expansion amount of the expansion base is converted into the reduction of the height of the limiting arc plate through the retraction mechanism. By choosing a material with a suitable coefficient of thermal expansion a2As the material of the expansion mount. Make to keep there being spacing clearance d between spacing arc board and the gag lever post all the time to guaranteed under from non-operating condition to operating condition, adjustable stator angle can keep the uniformity, can not take place the card between spacing arc board and the gag lever post yet and die simultaneously, thereby can increase the reliability of engine.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 shows a schematic view of a typical adjustable vane adjustment mechanism in a prior art aircraft engine;
FIG. 2 is a schematic view of another angle of an adjustable vane adjustment mechanism typical of prior art aircraft engines;
FIG. 3 shows a schematic view of a prior art link stop arrangement;
FIG. 4 is a schematic diagram illustrating one embodiment of the present link retainer device;
FIG. 5 is a schematic view of the present link ring position limiter viewed from another angle.
Detailed Description
The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and are not intended to limit the scope of the present disclosure. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.
It should be noted that, where used, the following description of upper, lower, left, right, front, rear, top, bottom, positive, negative, clockwise, and counterclockwise are used for convenience only and do not imply any particular fixed orientation. In fact, they are used to reflect the relative position and/or orientation between the various parts of the object.
It is noted that these and other figures which follow are merely exemplary and not drawn to scale and should not be considered as limiting the scope of the invention as it is actually claimed. Further, the conversion methods in the different embodiments may be appropriately combined.
It should be noted that the reference numerals described later and the reference numerals in the background art use different labeling systems, and there is no correlation between the reference numerals.
Fig. 4 is a schematic view showing one embodiment of the link stopper, and fig. 5 is a schematic view of the link stopper viewed from another angle. Wherein, link ring stop device includes gag lever post 1, inflation base 2 and spacing arc 3. The limiting rod 1 is disposed through the coupling half ring 4 as shown in the figure, and has a limiting end 10 disposed toward the casing 5.
The expansion base 2 is arranged on the casing 5 corresponding to the position of the limiting end 10, thereby being arranged opposite to the limiting rod 1. The limiting arc plate 3 is supported on the expansion base 2 by the retraction mechanism 21, and the initial height H of the retraction mechanism 21 is configured to maintain a limiting gap d between the top surface 30 of the limiting arc plate 3 and the limiting end 10, so that a small gap exists between the limiting rod 1 and the top surface 30 of the limiting arc plate 3 in an unworked cold state, and therefore the limiting rod 1 and the limiting arc plate 3 cannot be jammed in the cold state on the premise that the angle of the adjustable guide vane is consistent.
In the working state, the casing 5 will expand by heat, so that the radius of the casing 5 increases, and in order to ensure that the spacing gap d is still kept between the spacing rod 1 and the spacing arc plate 3, the thermal expansion coefficient a of the casing 5 material1Coefficient of thermal expansion a with the material of the expansion base 22Satisfies the following formula (1):
Figure BDA0002479086350000051
wherein R is1Radius R of the casing 5 at normal temperature2The radius of the limiting arc plate 3 is at normal temperature, and L is the initial of the retracting mechanism 21 at normal temperatureThe length, H, and Δ T are the initial height of the retracting mechanism 21 at room temperature and the temperature change amount, respectively. It is understood that the temperature change Δ T referred to in the foregoing is a temperature change value from a non-operating state (i.e., at normal temperature) to an operating state. By the above formula, it can be ensured that the radial expansion amount of the casing 5 and the height change of the expansion mechanism 21 caused by the radial deformation amount of the expansion base 2 at a constant temperature change Δ T are mutually offset, and the formula (1) is simplified to obtain the formula (2):
Figure BDA0002479086350000052
to ensure the offset of the deformation, the parameter R needs to be adjusted1Ha1＝L2a2。
When the casing 5 is heated to expand, the expansion base 2 is also heated to expand, and at the moment, the heated expansion amount of the expansion base 2 is converted into the reduction of the height of the limiting arc plate 3 through the retraction mechanism 21. By choosing a material with a suitable coefficient of thermal expansion a2As the material of the expansion base 2. Make to keep there being spacing clearance d between spacing arc plate 3 and the gag lever post 1 throughout to guaranteed that from non-operating condition to under the operating condition, adjustable stator angle can keep the uniformity, can not take place the card to die between spacing arc plate 3 and the gag lever post 1 simultaneously, thereby can increase the reliability of engine.
The aforementioned coefficient of thermal expansion a is illustrated for a specific example as follows1And coefficient of thermal expansion a2The relationship between them.
Example 1
The material of the M152 stainless steel casing 5 is selected, and the radius R of the casing 51The setting is 320mm, the material of the expansion base 2 is also selected to be M152 stainless steel, the initial height H of the retraction mechanism 21 at normal temperature is 10mm, and the initial length L of the retraction mechanism 21 at normal temperature is 55 mm.
And adjusting the initial limit clearance d between the limit rod 1 and the limit arc plate 3 to be 0.1-0.2 mm at the normal temperature (25 ℃).
When the temperature variation Δ T is between 75 and 375 degrees celsius, i.e. the operating temperature is between 100 and 400 degrees celsius (normally, the adjustable level of the aircraft engine corresponds to the ambient temperature), the variation of the limit clearance d is as shown in the following table one:
Figure BDA0002479086350000061
watch 1
As shown in the table, at 100-400 ℃, the expansion amount of the casing 5 and the expansion amount of the expansion base 2 are considered, so that the limiting gap d between the limiting rod 2 and the limiting arc plate 3 can be kept between 0.1 mm and 0.2mm under the condition of all working conditions.
It is understood that in the foregoing embodiment, for the convenience of calculation, M152 stainless steel is selected as the material of the expansion base 2 and the casing 5, and in some other embodiments, the material of the expansion base 2 may have other thermal expansion coefficients a2Satisfies the formula: r1Ha1＝L2a2The material of the expansion base 2 may be, for example, in some embodiments, a nickel-based superalloy such as lnco718 or titanium-aluminum alloy TC 4.
While one embodiment of the present link stop is described above, in other embodiments of the present link stop, the link stop may have more details than the embodiments described above in many respects, and at least some of these details may vary widely. At least some of these details and variations are described below in several embodiments.
In one embodiment of the link ring retainer, the expansion base 2 is made of M152 stainless steel, and in some other embodiments, the material of the expansion base 2 may be ni-based high temperature alloy such as lnco718 or titanium aluminum alloy TC 4.
In one embodiment of the link ring limiting device, the retracting mechanism 21 is an X-shaped leg retracting mechanism as shown in the figure, and specifically, it includes a first leg structure 211 and a second leg structure 212 which are crossed and hinged, wherein both ends of the first leg structure 211 are respectively connected with one end of the expansion base 2 and one end of the limiting arc plate 3, and the second leg structure 212 is respectively connected with the other end of the expansion base 2 and the other end of the limiting arc plate 3, so that when the expansion base 2 is heated and expands along the circumferential direction of the casing 5, the first leg structure 211 and the second leg structure 212 are respectively pulled to rotate along the hinged part, thereby reducing the overall height H of the retracting mechanism 21, so that the limiting arc plate 3 is reduced along with the reduction of the overall height H of the retracting mechanism 21. In some other embodiments, the retraction mechanism 21 may be a support structure with other forms that can adjust the height following the expansion of the expansion base 2, such as a multi-layer combined X-leg retraction mechanism.
In one embodiment of the link ring limiting device, the circle of the limiting arc plate 3, the circle of the casing 5 and the circle of the link half ring 4 are concentric, so as to further ensure that the limiting arc plate 3, the casing 5 and the link half ring 4 can synchronously expand/cool and contract when the work is heated.
In one embodiment of the link ring limiting device, the expansion base 2 and the casing 5 are in close contact, so that when the casing 5 expands due to heat, the heat can be transferred to the expansion base 2. In one embodiment, there is a welded connection between the expansion base 2 and the casing 5.
In one embodiment of the link ring limiting device, a limiting sleeve 11 is arranged at one end of the limiting rod 1 after penetrating through the link half ring 4, so that the limiting gap d can be adjusted by replacing different limiting sleeves.
In one embodiment of the link ring limiting device, it is suitable for an environment in which the temperature variation Δ T is between 75 and 375 degrees celsius, i.e. corresponding to the ambient temperature to which the aircraft engine can be stepped under normal conditions.
The link ring limiting device in one or more embodiments is suitable for an adjustable vane adjusting mechanism, as shown in fig. 4 to 5, the adjustable vane adjusting mechanism includes a bushing 6, a rocker arm 7 and a link half ring 4, and two ends of the rocker arm 7 are respectively connected with the bushing 6 and the link half ring 4.
In one embodiment of the adjustable vane adjusting mechanism, the link half rings 4 are connected by the link ring overlapping section 40 to form a complete ring-shaped link ring, and the link ring limiting means is provided in plural numbers along the circumferential direction of the complete ring-shaped link ring, so as to limit at plural positions in the circumferential direction.
The adjustable guide vane adjusting mechanism in one or more of the foregoing embodiments is applied to a gas turbine, and the operating state and the non-operating state as described above refer to an operating state and/or a non-operating state of the gas turbine.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.

Claims (10)

1. A link ring stop device, comprising:
the limiting rod penetrates through the linkage half ring and is provided with a limiting end arranged towards the casing;
the expansion base is arranged on the casing at a position corresponding to the limiting end; and
the limiting arc plate is supported on the expansion base by a retraction mechanism, and a limiting gap is kept between the top surface of the limiting arc plate and the limiting end;
wherein, in order to maintain the limit clearance, the thermal expansion coefficient a of the casing material1Coefficient of thermal expansion a with the expansion base material2Satisfies the following formula:
R1Ha1＝L2a2；
wherein R is1The radius of the case at normal temperature, the initial height of the retraction mechanism at normal temperature and the initial length of the retraction mechanism at normal temperature are shown as H.
2. A link ring stop according to claim 1 wherein the expansion base is made of M152 stainless steel.
3. The link ring restraint of claim 1 wherein the retraction mechanism is an X-leg retraction mechanism.
4. The retainer of claim 1, wherein the retaining arc plate, the case, and the half linkage ring are concentric.
5. A link ring retainer as recited in claim 1, wherein said expansion base is in intimate contact with said case.
6. The link ring limiting device according to claim 1, wherein a limiting sleeve is provided at an end of the limiting rod after passing through the link half rings, and the limiting sleeve has the limiting end.
7. The link ring stop of claim 1, wherein the link ring stop is adapted for use in an environment having a temperature variation between 75 and 375 degrees celsius.
8. An adjustable guide vane adjusting mechanism comprises a bushing, a rocker arm and a linkage half ring, wherein two ends of the rocker arm are respectively connected with the bushing and the linkage half ring, and the linkage ring limiting device as claimed in any one of claims 1 to 7 is arranged between the linkage half ring and a casing.
9. The adjustable vane adjustment mechanism of claim 8, wherein the linkage half rings are connected by linkage ring overlapping sections to form a complete ring-shaped linkage ring, and the linkage ring limiting device is provided in plurality along a circumferential direction of the linkage ring.
10. A gas turbine comprising an adjustable vane adjustment mechanism as claimed in any one of claims 8 to 9.
CN202010373650.6A 2020-05-06 2020-05-06 Gas turbine, adjustable guide vane adjusting mechanism and linkage ring limiting device thereof Pending CN113623271A (en)

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US3975901A (en) * 1974-07-31 1976-08-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Device for regulating turbine blade tip clearance
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JP2016156344A (en) * 2015-02-25 2016-09-01 三菱日立パワーシステムズ株式会社 Variable stationary blade drive device and axial flow fluid machinery
CN209510724U (en) * 2019-01-31 2019-10-18 中国航发商用航空发动机有限责任公司 Compressor linkage ring position-limit mechanism and compressor linkage ring assemblies
CN209510710U (en) * 2019-01-31 2019-10-18 中国航发商用航空发动机有限责任公司 Compressor linkage ring position-limit mechanism and compressor linkage ring assemblies

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3975901A (en) * 1974-07-31 1976-08-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Device for regulating turbine blade tip clearance
US5035572A (en) * 1989-04-21 1991-07-30 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Arrangement for adjusting guide blades
US6514041B1 (en) * 2001-09-12 2003-02-04 Alstom (Switzerland) Ltd Carrier for guide vane and heat shield segment
EP1531237A2 (en) * 2003-11-14 2005-05-18 Rolls-Royce Plc Supporting an actuating ring for variable guide vanes of a compressor
FR2879684A1 (en) * 2004-12-16 2006-06-23 Snecma Moteurs Sa Turbomachine e.g. compressor, for jet aircraft engine, has station including diffuser blades, each having conical housing extending transversally to pivot axis, and tie rod with conical portion engaging in conical housing and fixed to pivot
FR2882570A1 (en) * 2005-02-25 2006-09-01 Snecma Moteurs Sa AUB CONTROL DEVICE WITH VARIABLE SHIFT IN A TURBOMACHINE
FR2902454A1 (en) * 2006-06-16 2007-12-21 Snecma Sa TURBOMACHINE STATOR COMPRISING A FLOOR OF ADJUSTERS ADJUSTED BY A ROTATING CROWN WITH AUTOMATIC CENTERING
CN101063415A (en) * 2007-05-24 2007-10-31 岂兴明 Executing mechanism of turbo blade tip gap rapid initiative control system
FR2920469A1 (en) * 2007-08-30 2009-03-06 Snecma Sa TURBOMACHINE VARIABLE CALIBRATION
CN102410088A (en) * 2011-12-22 2012-04-11 中国船舶重工集团公司第七�三研究所 Adjustable guide vane system of gas turbine power turbine
US20160090856A1 (en) * 2014-09-26 2016-03-31 Rolls-Royce Deutschland Ltd & Co Kg Stator vane adjusting device of a gas turbine
CN104533540A (en) * 2014-11-14 2015-04-22 沈阳黎明航空发动机(集团)有限责任公司 Device for guaranteeing concentricity of actuating ring and compressor casing
JP2016156344A (en) * 2015-02-25 2016-09-01 三菱日立パワーシステムズ株式会社 Variable stationary blade drive device and axial flow fluid machinery
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CN209510710U (en) * 2019-01-31 2019-10-18 中国航发商用航空发动机有限责任公司 Compressor linkage ring position-limit mechanism and compressor linkage ring assemblies

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