WO2016181420A1 - アクセサリギアボックスのマウント機構 - Google Patents
アクセサリギアボックスのマウント機構 Download PDFInfo
- Publication number
- WO2016181420A1 WO2016181420A1 PCT/JP2015/002350 JP2015002350W WO2016181420A1 WO 2016181420 A1 WO2016181420 A1 WO 2016181420A1 JP 2015002350 W JP2015002350 W JP 2015002350W WO 2016181420 A1 WO2016181420 A1 WO 2016181420A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- pair
- bracket
- link
- brackets
- accessory gearbox
- Prior art date
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 34
- 241001247986 Calotropis procera Species 0.000 claims description 17
- 239000002184 metal Substances 0.000 claims description 10
- 238000013016 damping Methods 0.000 abstract description 2
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
- B64D27/402—Arrangements for mounting power plants in aircraft comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
-
- 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
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F1/00—Springs
- F16F1/36—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers
- F16F1/373—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers characterised by having a particular shape
- F16F1/3732—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers characterised by having a particular shape having an annular or the like shape, e.g. grommet-type resilient mountings
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- 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
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/31—Retaining bolts or nuts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/40—Transmission of power
- F05D2260/403—Transmission of power through the shape of the drive components
- F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Definitions
- the present invention relates to a mount mechanism for attaching an accessory gear box to an engine case in an aero engine.
- An aero engine accessory gearbox is installed in the engine case and distributes the power extracted from the engine core to various auxiliary machines.
- the accessory gearbox extends in the circumferential direction of the engine case, and is attached to the engine case by a plurality of mounting mechanisms scattered in the circumferential direction of the engine case.
- Patent Document 1 discloses a pair of mount mechanisms (so-called side hangers) disposed at both ends of an accessory gear box.
- Each mounting mechanism includes a first bracket fixed to the engine case, a second bracket fixed to the accessory gear box, and a link having both ends connected to the first bracket and the second bracket by pins.
- a metal bush is disposed between each bracket and the pin and between the link and the pin.
- an annular vibration isolator for example, rubber
- a bush it is necessary to use a very large vibration isolator in order to absorb a large load and vibration when the blade is off.
- Such a large vibration isolator moves the accessory gear box away from the engine case and interferes with the nacelle (cowl) that houses the accessory gear box and the aero engine.
- an object of the present invention is to provide a mounting mechanism for an accessory gear box that can use a relatively small vibration isolator.
- the accessory gearbox mounting mechanism of the present invention is a mounting mechanism for attaching an accessory gearbox to an engine case in an aero engine, and is fixed to one of the engine case and the accessory gearbox.
- the pair of first brackets spaced apart from each other in the circumferential direction of the engine case and the pair of first brackets are connected to each other, and both ends are connected to the pair of first brackets by a pair of first pins.
- a ring-shaped vibration isolator inserted into each of the pair of first pins, the vibration isolator being held by at least one of the first bracket and the end of the link, and the engine A second bracket fixed to the other of the case and the accessory gearbox, wherein the pair of first gears And a second bracket connected to the link by a second pin between the brackets, characterized in that.
- the load and vibration at the time of blade off transmitted from the engine case to the mount mechanism are distributed to the pair of first brackets. Therefore, a relatively small vibration isolator can be used for the pair of pins connecting the first bracket and both ends of the link. Thereby, the load and vibration transmitted to the accessory gear box can be suppressed, and the accessory gear box can be reduced in size and weight. Moreover, since the vibration isolator is held by at least one of the first bracket and the end of the link, the mount mechanism can be designed flexibly according to the load and vibration.
- an accessory gearbox mounting mechanism that can use a relatively small vibration isolator.
- FIG. 1 is a front view of an aircraft engine that employs a mounting mechanism for an accessory gearbox according to an embodiment of the present invention. It is a side view of the aircraft engine shown in FIG. It is a side view of the aircraft engine of a modification. It is a front view of a mount mechanism.
- FIG. 5 is a sectional view taken along line VV in FIG. 4. It is a disassembled perspective view of a pair of 1st bracket and a link.
- FIGS. 1 and 2 show an aero engine 1 employing an accessory gearbox mounting mechanism 3 according to an embodiment of the present invention.
- the aircraft engine 1 is housed in a nacelle (cowl) 10 and includes an engine core 2 and an accessory gear box 11.
- the engine core 2 includes an engine case 21 that houses the rotary assembly.
- the engine case 21 includes a fan case 22, a compressor case 23, a combustion chamber case 24, and a turbine case 25 as shown in FIG.
- the accessory gear box 11 extends in the circumferential direction of the engine case 21, and is attached to the engine case 21 of the engine core 2 by a pair of mounting mechanisms 3 disposed at both ends of the accessory gear box 11.
- the accessory gear box 11 is attached to the fan case 22.
- the accessory gear box 11 may be attached to the compressor case 23.
- a plurality of auxiliary machines 12 are attached to the accessory gear box 11.
- each mount mechanism 3 will be described in detail with reference to FIGS.
- the accessory gear box 11 may be attached to the compressor case 23 as described above, it goes without saying that the fan case 22 described below may be replaced with the compressor case 23 in that case.
- Each mount mechanism 3 includes a pair of first brackets 4 fixed to the fan case 22 and a second bracket 8 fixed to the accessory gear box 11.
- the first bracket 4 is fixed to the fan case 22 by, for example, an unillustrated fixing member (for example, a bolt).
- the first bracket 4 may be provided integrally with the fan case 22.
- each first bracket 4 may include only a pair of first lugs 41 described later without including a land 42 described later.
- the second bracket 8 is fixed to the accessory gear box 11 by being provided integrally with the housing of the accessory gear box 11, for example.
- the second bracket 8 may be fixed to the accessory gear box 11 by a fixing member such as a bolt.
- the pair of first bracket 4 and second bracket 8 are connected by a link 5.
- the link 5 is a linear member having a constant thickness.
- the pair of first brackets 4 are separated from each other in the circumferential direction of the fan case 22.
- Each first bracket 4 includes a pair of first lugs 41 that sandwich the end of the link 5, and a plate-like land 42 that is in surface contact with the fan case 22. In other words, the land 42 is bent along the fan case 22.
- each first bracket 4 has a U shape that opens toward the other first bracket 4.
- the land 42 has a pair of arm portions 42a parallel to each other on both sides of the opening.
- a pair of first lugs 41 protrude from these arm portions 42a.
- the arm portion 42 a of the land 42 in one first bracket 4 and the arm portion 42 a of the land 42 in the other first bracket 4 are connected to each other by a pair of connectors 43.
- the pair of first brackets 4 and the pair of connectors 43 constitute a bracket unit having a long hole 45 at the center.
- the long hole 45 is for avoiding interference between the bracket unit and the link 5.
- the connector 43 is a plate-like member having the same thickness as the land 42 that is bent along the fan case 22 so as to come into surface contact with the fan case 22.
- the link 5 extends so as to connect the pair of first brackets 4 to each other.
- the link 5 may be bent along the fan case 22. Both ends of the link 5 are connected by a pair of first brackets 4 and a pair of first pins 6.
- first lugs 41 and the ends of the links 5 are respectively provided with holding holes 41a and 51 in which the rubber bushes 7 are accommodated.
- An outer sleeve 65 is fitted in each of the holding holes 41a and 51.
- three inner sleeves 63 are fitted to the first pin 6.
- Each rubber bush 7 is joined to the inner sleeve 63 and the outer sleeve 65 by, for example, an adhesive.
- the material of the rubber bush 7 is not particularly limited, and various materials can be used.
- the rubber bush 7 is configured such that the spring constant in the radial direction of the first pin 6 is higher than the spring constant in the axial direction of the first pin 6.
- Such anisotropy of the spring constant can be realized by the direction of the additive added when the rubber bush 7 is manufactured. Due to the anisotropy of the spring constant, the required spring constant and damping rate can be arbitrarily adjusted.
- the spring constant of the rubber bush 7 in the radial direction of the first pin 6 is non-linear such that the spring constant increases exponentially with respect to strain, for example.
- the first pin 6 is a bolt having a shaft portion 61 and a head portion 62 having a thread 61a formed at least at the tip.
- a nut 64 is engaged with the screw thread 61a.
- the nut 64 serves to sandwich the three inner sleeves 63 with the head 62.
- the structure of the 1st pin 6 is not necessarily limited to this, It can change suitably.
- the second bracket 8 is connected to the link 5 by a second pin 9 between the pair of first brackets 4.
- the second bracket 8 includes a pair of second lugs 81 that sandwich the central portion of the link 5.
- a metal bush 91 inserted through the second pin 9 is held in each of the second bracket 8 and the link 5. That is, the second bracket 8 and the link 5 are provided with fitting holes 82 and 52 into which the metal bush 91 is fitted, respectively.
- the load and vibration at the time of blade off transmitted from the fan case 22 to each mount mechanism 3 are distributed to the pair of first brackets 4. Therefore, a relatively small rubber bush 7 can be used for the pair of first pins 6 that connect the first bracket 4 and both ends of the link 5. Thereby, the load and vibration transmitted to the accessory gear box 11 can be suppressed, and the accessory gear box 11 can be reduced in size and weight.
- the pair of first brackets 4 may be independent of each other.
- a pair of 1st bracket 4 comprises the single bracket unit with a pair of connector 43 like this embodiment, a pair of 1st bracket 4 can be handled integrally.
- the elongated hole 45 is formed by the opening of the land 42 and the gap between the connectors 43, the link 5 can be linear even if the bracket unit is bent along the fan case 22. Therefore, the manufacturing cost of the link 5 can be reduced.
- the metal bush 91 is held in each of the second bracket 8 and the link 5, the cost can be reduced on the second bracket 8 side as compared with the case where the rubber bush 7 is used.
- the mount mechanism 3 can be easily assembled.
- each first bracket 4 does not necessarily have a pair of first lugs 41, and may have only one first lug 41. In this case, both ends of the link 5 may be bifurcated so as to sandwich the first lug 41.
- the link 5 may be composed of two pieces that sandwich the first lug 41 and the second lug 81. Good.
- the link 5 can be simplified. The shape can be a single part, and the cost can be reduced.
- the rubber bush 7 is not necessarily held by each of the pair of first lugs 41 and the end portions of the link 5, as long as it is held by at least one of the first bracket 4 and the end portions of the link 5. Good. Thus, if the rubber bush 7 is held by at least one of the first bracket 4 and the end of the link 5, the mount mechanism 3 can be designed flexibly according to the load and vibration.
- annular vibration isolator of the present invention is not limited to the rubber bush 7.
- a damper-type structure using a liquid may be used, or a metal spring may be used.
- first bracket 4 is fixed to the engine case 21 and the second bracket 8 is fixed to the accessory gear box 11.
- first bracket 4 is fixed to the accessory gear box 11.
- the second bracket 8 may be fixed to the engine case 21.
- the second bracket 8 and the link may each hold a rubber bush 7 instead of the metal bush 91 depending on the load and vibration when the blade is off (however, the first bracket 4 is an accessory gear box). 11 and the second bracket 8 is fixed to the engine case 21).
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Vibration Prevention Devices (AREA)
- Springs (AREA)
- General Details Of Gearings (AREA)
Abstract
Description
本発明は上述した実施形態に限定されるものではなく、本発明の要旨を逸脱しない範囲で種々の変形が可能である。
11 アクセサリギアボックス
21 エンジンケース
3 マウント機構
4 第1ブラケット
41 第1ラグ
41a 保持穴
42 ランド
42a アーム部
43 コネクタ
5 リンク
51 保持穴
6 第1ピン
61 軸部
61a ネジ山
62 頭部
63 内側スリーブ
64 ナット
65 外側スリーブ
7 ゴムブッシュ(防振体)
8 第2ブラケット
81 第2ラグ
9 第2ピン
91 金属ブッシュ
Claims (7)
- 航空エンジンにおけるエンジンケースへアクセサリギアボックスを取り付けるためのマウント機構であって、
前記エンジンケースと前記アクセサリギアボックスの一方に固定された、前記エンジンケースの周方向に互いに離間する一対の第1ブラケットと、
前記一対の第1ブラケット同士をつなぐように延び、両端部が前記一対の第1ブラケットと一対の第1ピンによって連結されたリンクと、
前記一対の第1ピンのそれぞれに挿通される環状の防振体であって、前記第1ブラケットと前記リンクの端部の少なくとも一方に保持される防振体と、
前記エンジンケースと前記アクセサリギアボックスの他方に固定された第2ブラケットであって、前記一対の第1ブラケットの間で第2ピンによって前記リンクに連結された第2ブラケットと、
を備える、アクセサリギアボックスのマウント機構。 - 前記防振体は、ゴムブッシュであり、
前記ゴムブッシュは、前記第1ピンの径方向におけるバネ定数が前記第1ピンの軸方向におけるバネ定数よりも高くなるように構成されている、請求項1に記載のアクセサリギアボックスのマウント機構。 - 前記一対の第1ブラケットのそれぞれは、前記リンクの端部を挟み込む一対の第1ラグを含み、
前記第2ブラケットは、前記リンクの中央部を挟み込む一対の第2ラグを含む、請求項1または2に記載のアクセサリギアボックスのマウント機構。 - 前記防振体は、前記一対の第1ラグと前記リンクの端部のそれぞれに保持されており、前記第1ピンと嵌合する内側スリーブと、前記第1ラグまたは前記リンクに設けられた保持穴と嵌合する外側スリーブとに接合されている、請求項3に記載のアクセサリギアボックスのマウント構造。
- 前記第1ピンは、少なくとも先端にネジ山が形成された軸部と頭部を有するボルトであり、前記ネジ山には、前記頭部との間で複数の前記内側スリーブを挟持するナットが係合している、請求項4に記載のアクセサリギアボックスのマウント構造。
- 前記一対の第1ブラケットのそれぞれは、他方の第1ブラケットに向かって開口するU字状のランドを含み、前記一対の第1ラグは、前記ランドにおける互いに平行なアーム部から突出しており、
一方の前記第1ブラケットにおける前記ランドの前記アーム部と他方の前記第1ブラケットにおける前記ランドの前記アーム部とを接続する一対のコネクタをさらに備える、請求項3~5のいずれか一項に記載のアクセサリギアボックスのマウント機構。 - 前記第2ブラケットおよび前記リンクのそれぞれには、前記第2ピンに挿通される金属ブッシュが保持されている、請求項1~6のいずれか一項に記載のアクセサリギアボックスのマウント機構。
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP15891748.4A EP3296215B1 (en) | 2015-05-08 | 2015-05-08 | Mount mechanism for accessory gearbox |
US15/572,337 US10266274B2 (en) | 2015-05-08 | 2015-05-08 | Mount mechanism of accessory gearbox |
JP2017517449A JP6564455B2 (ja) | 2015-05-08 | 2015-05-08 | アクセサリギアボックスのマウント機構 |
PCT/JP2015/002350 WO2016181420A1 (ja) | 2015-05-08 | 2015-05-08 | アクセサリギアボックスのマウント機構 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/JP2015/002350 WO2016181420A1 (ja) | 2015-05-08 | 2015-05-08 | アクセサリギアボックスのマウント機構 |
Publications (1)
Publication Number | Publication Date |
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WO2016181420A1 true WO2016181420A1 (ja) | 2016-11-17 |
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PCT/JP2015/002350 WO2016181420A1 (ja) | 2015-05-08 | 2015-05-08 | アクセサリギアボックスのマウント機構 |
Country Status (4)
Country | Link |
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US (1) | US10266274B2 (ja) |
EP (1) | EP3296215B1 (ja) |
JP (1) | JP6564455B2 (ja) |
WO (1) | WO2016181420A1 (ja) |
Cited By (2)
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CN109027424A (zh) * | 2017-06-12 | 2018-12-18 | 中国船舶重工集团公司第七研究院 | 一种圆筒型管路隔振器及其刚度计算的方法 |
CN117366205A (zh) * | 2023-12-08 | 2024-01-09 | 南京传仕重工科技有限公司 | 一种冷却水塔用齿轮箱 |
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US11261795B2 (en) * | 2018-10-18 | 2022-03-01 | Rolls-Royce North American Technologies, Inc. | Dual mode starter generator |
US11015532B2 (en) * | 2018-10-18 | 2021-05-25 | Rolls-Royce North American Technologies, Inc. | Parallel starter/generator and air turbine starter |
US12116936B2 (en) | 2023-01-20 | 2024-10-15 | Honeywell International Inc. | Mounting system for gearbox including corrugated bushing |
EP4403750A1 (en) * | 2023-01-20 | 2024-07-24 | Honeywell International Inc. | Mounting system for gearbox including corrugated bushing |
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CN117366205B (zh) * | 2023-12-08 | 2024-02-20 | 南京传仕重工科技有限公司 | 一种冷却水塔用齿轮箱 |
Also Published As
Publication number | Publication date |
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US20180118357A1 (en) | 2018-05-03 |
EP3296215A1 (en) | 2018-03-21 |
JP6564455B2 (ja) | 2019-08-21 |
US10266274B2 (en) | 2019-04-23 |
EP3296215A4 (en) | 2018-10-03 |
JPWO2016181420A1 (ja) | 2018-02-22 |
EP3296215B1 (en) | 2020-02-26 |
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