JPH04209901A - Moving blade and manufacture thereof - Google Patents
Moving blade and manufacture thereofInfo
- Publication number
- JPH04209901A JPH04209901A JP40975690A JP40975690A JPH04209901A JP H04209901 A JPH04209901 A JP H04209901A JP 40975690 A JP40975690 A JP 40975690A JP 40975690 A JP40975690 A JP 40975690A JP H04209901 A JPH04209901 A JP H04209901A
- Authority
- JP
- Japan
- Prior art keywords
- rotor blade
- blade body
- moving blade
- partition plate
- same direction
- 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.)
- Pending
Links
- 238000004519 manufacturing process Methods 0.000 title claims description 22
- 239000000835 fiber Substances 0.000 claims abstract description 31
- 239000011347 resin Substances 0.000 claims abstract description 30
- 229920005989 resin Polymers 0.000 claims abstract description 30
- 238000005192 partition Methods 0.000 claims abstract description 18
- 238000010030 laminating Methods 0.000 claims abstract description 8
- 239000000463 material Substances 0.000 claims description 24
- 238000000034 method Methods 0.000 claims description 12
- 238000000748 compression moulding Methods 0.000 claims description 10
- 238000007731 hot pressing Methods 0.000 claims description 2
- 238000012360 testing method Methods 0.000 description 6
- 238000005452 bending Methods 0.000 description 3
- 230000001788 irregular Effects 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 238000010008 shearing Methods 0.000 description 3
- 238000011835 investigation Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 239000012779 reinforcing material Substances 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000001934 delay Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000011981 development test Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000007730 finishing process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 239000002990 reinforced plastic Substances 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
［０００１１ [00011
【産業上の利用分野］本発明は、航空用、産業用ガスタ
ービン等のファンや圧縮機に使用する動翼（取付は角を
変えることができる可変動翼も含む）及び該動翼の製造
方法に関するものである。
［０００２］
【従来の技術】航空用、産業用ガスタービン等のファン
や圧縮機に使用されている動翼（可変動翼を含む）の製
造方法としては、下記の如き方法が採用されていた。
［０００３］即ちチタン、ステンレス、アルミニウム等
の金属を素材として、鍛造加工、機械加工、仕上加工、
コーティング加工の手順で製造する動翼製造方法がある
。
［０００４］上記方法以外に、流体に面する動翼本体部
分と取付は部である翼根部分とを、板状のプリプレグ材
（強化プラスチック材）を積層して圧縮成形することに
より動翼を製造する方法もある。
［０００５］[Industrial Application Field] The present invention relates to rotor blades (including variable blades whose angles can be changed) used in fans and compressors of aviation and industrial gas turbines, and the manufacture of the rotor blades. It is about the method. [0002] [Prior Art] The following method has been adopted as a method for manufacturing moving blades (including variable blades) used in fans and compressors of aircraft and industrial gas turbines, etc. . [0003] That is, forging, machining, finishing, etc. using metals such as titanium, stainless steel, and aluminum as raw materials.
There is a method for manufacturing rotor blades using a coating process. [0004] In addition to the above method, the rotor blade can be formed by laminating and compression molding plate-shaped prepreg material (reinforced plastic material) on the rotor blade body portion facing the fluid and the blade root portion, which is the attachment portion. There are also ways to manufacture it. [0005]
【発明が解決しようとする課題】しかしながら前者の動
翼加工製造方法では、製造期間が長く、素材のコストが
高く且つ加工工程が多いので高価になり、重量が重い、
等の問題点があった。
［０００６］又後者の動翼の製造方法は、前者の動翼製
造方法が有する問題点をなくし得るが、以下のような問
題点があった。
［０００７］■動翼本体部分と翼根部分との間の厚みが
顕著に変化しているので、動翼本体部分及び翼根部分に
おける板状のプリプレグ材に圧縮成形中に掛る圧力を均
等化することができず、そのために作用圧力にバラツキ
が生じて板状のプリプレグ材に不均一な圧力が掛ること
になり、この圧力のバラツキ（不均一）により生ずる圧
力差により溶融樹脂の流動が圧力の高い方から低い方に
不規則に発生し、この流動により強化材であるファイバ
ー（ｆ ｉ ｂｅ ｒ）（樹脂繊維）の流動方向が不規
則なって乱れ（渦巻き等の不整現象）が生じる。
［０００８］■上記フアイバーの流動方向の乱れにより
強度上必要とされているファイバーの同一向きの方向性
を得ることができず、そのために、強度が著しく低下し
所望の強度が得られない。
［０００９］■所望の強度を得るために、実験し分析し
その結果により条件を変えて更に実験や分析を繰返すと
いう試行錯誤の作業を行なわねばならず、テストの時間
に費やす作業及び時間が増えて、コストアップや製作の
遅れの原因となる。
［００１０１本発明は、上述の実情に鑑み、動翼の加工
工程を減少して製造時間を短縮して、コストダウンと軽
量化を図り、更にファイバーの不整現象を防止して振動
減衰率、比強度、比剛性の向上をなし得る、動翼及び該
動翼の製造方法を提供することを目的とするものである
。
［００１１１[Problems to be Solved by the Invention] However, the former rotor blade manufacturing method requires a long manufacturing period, high material costs, and many processing steps, making it expensive, heavy, and heavy.
There were problems such as. [0006]Although the latter method of manufacturing a rotor blade can eliminate the problems of the former method of manufacturing a rotor blade, it has the following problems. [0007] ■ Since the thickness between the rotor blade body and the blade root portion changes significantly, the pressure applied to the plate-shaped prepreg material in the rotor blade body and the blade root portion during compression molding is equalized. As a result, variations in working pressure occur and non-uniform pressure is applied to the plate-shaped prepreg material, and the pressure difference caused by this variation (non-uniformity) in pressure causes the flow of molten resin to increase in pressure. This flow occurs irregularly from high to low, and this flow causes the flow direction of the reinforcing material (fiber) (resin fiber) to become irregular, resulting in turbulence (irregular phenomena such as swirling). [0008] (2) Due to the disturbance in the flowing direction of the fibers, it is not possible to obtain the directionality of the fibers in the same direction, which is required for strength, so that the strength is significantly reduced and the desired strength cannot be obtained. [0009]■ In order to obtain the desired strength, it is necessary to perform trial and error work of experimenting and analyzing, changing the conditions according to the results, and repeating the experiment and analysis, which increases the work and time spent on testing. This can lead to increased costs and production delays. [00101] In view of the above-mentioned circumstances, the present invention reduces the number of processing steps for rotor blades, shortens manufacturing time, reduces cost and weight, and further improves the vibration damping rate and ratio by preventing fiber irregularities. It is an object of the present invention to provide a rotor blade and a method for manufacturing the rotor blade that can improve strength and specific rigidity. [00111
【課題を解決するための手段］請求項１の発明は、樹脂
繊維の向きが同一であるプリプレグ材から成る動翼本体
と、樹脂繊維の向きが動翼本体のプリプレグ材の樹脂繊
維と同じ向きのプリプレグ材から成り且つ動翼本体と連
なる翼根部と、該翼根部の反動翼本体側の略中央部から
動翼本体に挿入した仕切板と、からなることを特徴とす
る動翼、にかかるものである。
［００１２］請求項２の発明は、動翼本体と該動翼本体
と連なる翼根部とを、板状のプリプレグ材をその樹脂繊
維の向きを揃えて積層形成し、翼根部の反動翼本体側の
略中央部から仕切板を、動翼本体に亘り適宜挿入し、ホ
ットプレスにより圧縮成形して一体化することを特徴と
する動翼の製造方法、にかかるものである。
［００１３］
【作用】本発明によれば、従来の如く多数の加工工程行
なうことなく、簡単に動翼を製造できると共に、軽量化
できる。又板状のプリプレグ材のファイバーの不整現象
が発生することを防止でき、遠心応力に耐える強度の向
上が図れ、回転力によって発生する翼根部の剪断、曲げ
の各応力に耐える強度の向上が図れる。
［００１４］[Means for Solving the Problem] The invention of claim 1 provides a rotor blade body made of a prepreg material in which the resin fibers are oriented in the same direction, and a rotor blade body in which the resin fibers are oriented in the same direction as the resin fibers of the prepreg material of the rotor blade body. A rotor blade comprising: a blade root portion made of a prepreg material and connected to the rotor blade body; and a partition plate inserted into the rotor blade body from approximately the center of the blade root portion on the side of the reaction blade body. It is something. [0012] In the invention of claim 2, the rotor blade body and the blade root portion connected to the rotor blade body are formed by laminating plate-shaped prepreg materials with their resin fibers aligned in the direction, and the reaction blade body side of the blade root portion The present invention relates to a method for manufacturing a rotor blade, characterized in that a partition plate is appropriately inserted across the rotor blade body from approximately the center of the rotor blade, and the rotor blade is compression-molded and integrated by hot pressing. [0013] According to the present invention, a rotor blade can be easily manufactured without performing a large number of machining steps as in the conventional method, and the weight can be reduced. In addition, it is possible to prevent the occurrence of irregularities in the fibers of the plate-shaped prepreg material, improve the strength to withstand centrifugal stress, and improve the strength to withstand the shearing and bending stresses of the blade root caused by rotational force. . [0014]
【実施例】以下、本発明の実施例を図面を参照しつつ説
明する。
［００１５］図１は、本発明の動翼（可変動翼を含む）
を示す斜視図であり、又図２は図１のＩＩ力方向ら見た
図に相当し圧縮成形中の状態を示す図にして、図中１は
動翼本体、２は該動翼本体１と連なる翼根部であり、３
は該翼根部２から動翼本体１に亘り芯となる如く挿入し
た仕切板である。
［００１６］又図中４． ５． ６は強化材である樹脂
繊維４ａ、５ａ、６ａの向きが同一である板状のプリプ
レグ材であり、板状のプリプレグ材４と５から前記動翼
本体１が、又板状のプリプレグ材４と６から前記翼根部
２が夫々積層形成されている。
［００１７］前記せる動翼の製造方法について説明する
。
［００１８１図３に示す如く板状のプリプレグ材４゜５
．６を高さ方向に平行にしかもこれら板状のプリプレグ
材４． ５． ６の樹脂繊維４ａ、５ａ、６ａの向きを
同一方向にして（図２の矢印Ａ方向に揃えて）積層して
、動翼本体１及び該動翼本体１と連なる翼根部２を積層
形成し、該翼根部２の反動翼本体１側の略中央部分から
動翼本体１に亘り仕切板３を適宜挿入して（遠心応力が
一番掛る部分を補強する如く挿入して）、ホットプレス
による圧縮成形法により、加圧、加熱し一体化して動翼
を製造する。
［００１９］前記した如く動翼本体１及び翼根部２を積
層形成する板状のプリプレグ材４． ５． ６をそれら
の樹脂繊維４ａ、５ａ、６ａの向きを同一方向（図２の
矢印六方向）にして積層し且つ仕切板３を翼根部２から
動翼本体１に亘り各板状のプリプレグ材４． ５． ６
の面と平行に挿入しているので、圧縮成形時に生じる溶
融樹脂の流れが仕切板３に規制されて該仕切板３に沿い
垂直方向（図２の矢印Ａ方向）にしかも樹脂繊維４ａ、
５ａ、 ６ａの向きと同方向に動翼の厚みのある
方からない方に流れることになる。即ち動翼本体１並び
に翼根部２においては、中央部で上下方向に対称に仕切
板３で仕切られているので、該仕切板３で規制された状
態で図２の矢印Ａの方向に対称に溶融樹脂が圧力の高い
方から低い方に流れることになって左右の圧力バランス
がとれることになり、従って圧縮成形時に動翼を積層形
成する板状のプリプレグ材４． ５． ６に略均等な圧
力が掛ることになって樹脂繊維４ａ、５ａ、６ａの向き
に沿いこの向きを乱すことなく溶融樹脂が流動し、その
結果、樹脂繊維の一方向性が維持されて樹脂繊維（ファ
イバー）の不整現象の発生を防止でき強度の向上を図り
得る。
［００２０１即ち、動翼に生じる引張り、曲げ、捩れ、
剪断等の各応力に対し、強度の向上を図ることができる
。
［００２１］又圧縮成形時に動翼本体１と翼根部２とに
おける板状のプリプレグ材４． ５． ６に掛る圧力を
均一化できることにより、所望の強度を得るための内部
圧力状態の調査や調整等に費やす時間を大幅に短縮でき
て、特に開発試験中の動翼を製造する場合に最適であり
、しかも比強度及び比剛性が高いので過回転試験を高い
レベルで行なうことができる。
［００２２］尚、本発明は、上述の実施例にのみ限定さ
れるものではなく、例えば仕切板を金属板又はこれに類
する板材で形成すること、仕切板の動翼本体の挿入端部
分を先細り形状にすること等は任意であり、その他、本
発明の要旨を逸脱しない範囲内において種々変更を加え
得ることは勿論である。
［００２３］Embodiments Hereinafter, embodiments of the present invention will be described with reference to the drawings. [0015] FIG. 1 shows a moving blade (including a variable blade) of the present invention.
FIG. 2 is a perspective view showing the state during compression molding, which corresponds to the view seen from the II force direction in FIG. It is the wing root that is connected to 3.
is a partition plate inserted from the blade root portion 2 to the rotor blade body 1 so as to form a core. [0016] Also, 4 in the figure. 5. Reference numeral 6 denotes a plate-shaped prepreg material in which the resin fibers 4a, 5a, and 6a serving as reinforcing materials are oriented in the same direction. and 6, the blade root portions 2 are formed in layers. [0017] A method for manufacturing the rotor blade described above will be explained. [00181 As shown in Fig. 3, a plate-shaped prepreg material 4゜5
．． 6 parallel to the height direction and these plate-shaped prepreg materials 4. 5. The resin fibers 4a, 5a, and 6a of No. 6 are laminated in the same direction (aligned in the direction of arrow A in FIG. 2) to form a rotor blade body 1 and a blade root portion 2 connected to the rotor blade body 1. , the partition plate 3 is appropriately inserted from the approximate center of the blade root 2 on the reaction blade body 1 side to the rotor blade body 1 (inserted so as to reinforce the part where the centrifugal stress is most applied), and then hot pressed. Using the compression molding method, the rotor blades are manufactured by pressurizing, heating, and integrating. [0019] As described above, the plate-shaped prepreg material 4 for laminating the rotor blade body 1 and the blade root portion 2. 5. 6 are laminated with their resin fibers 4a, 5a, and 6a oriented in the same direction (six directions of arrows in FIG. 2), and the partition plate 3 is formed by forming each plate-shaped prepreg material 4 from the blade root 2 to the blade body 1. ．． 5. 6
Since the flow of the molten resin generated during compression molding is regulated by the partition plate 3, the flow of the molten resin is regulated by the partition plate 3, and the resin fibers 4a,
The flow will flow in the same direction as the directions of 5a and 6a from the side with the thicker rotor blades to the side with less thickness. That is, since the rotor blade body 1 and the blade root 2 are vertically symmetrically partitioned by a partition plate 3 at the center, the rotor blade body 1 and the blade root part 2 are partitioned symmetrically in the direction of arrow A in FIG. The molten resin flows from the high-pressure side to the low-pressure side, and the left and right pressures are balanced. Therefore, the plate-shaped prepreg material used to form the rotor blades by lamination during compression molding 4. 5. 6, the molten resin flows along the direction of the resin fibers 4a, 5a, 6a without disturbing the direction, and as a result, the unidirectionality of the resin fibers is maintained and the resin fibers It is possible to prevent the occurrence of irregularities in (fibers) and improve strength. [00201 That is, tension, bending, and twisting occurring in the rotor blade,
Strength can be improved against various stresses such as shearing. [0021] Also, during compression molding, plate-shaped prepreg material 4. 5. By being able to equalize the pressure applied to the blades, it is possible to significantly reduce the time spent investigating and adjusting the internal pressure state to obtain the desired strength, making it especially suitable for manufacturing rotor blades that are under development testing. Moreover, since the specific strength and specific rigidity are high, over-speed tests can be conducted at a high level. [0022] Note that the present invention is not limited to the above-described embodiments; for example, the partition plate may be formed of a metal plate or a similar plate material, and the insertion end portion of the partition plate into the rotor blade body may be tapered. It goes without saying that the shape can be changed arbitrarily, and various other changes can be made without departing from the gist of the present invention. [0023]
【発明の効果】以上説明したように、本発明の動翼及び
該動翼の製造方法によれば、下記の如き優れた効果を奏
し得る。
［００２４］■請求項１によれば、樹脂繊維の向きが同
一である板状のプリプレグ材を積層して動翼本体及び翼
根部を形成し且つこれら動翼本体及び翼根部の中央部に
仕切板を挿入してなるので、金属製の動翼に比べ安価に
製造できて軽量であり、比強度及び比剛性が高く、しか
も表面の仕上りが滑らかであるので空力性能が向上する
。
［００２５］■請求項１によれば、使用時に動翼に作用
する引張り、曲げ、捩れ、剪断等の各応力に対応できる
。
［００２６］■請求項２によれば、所望の強度を得るた
めに、圧縮成形時に動翼本体と翼根部とにおける作用圧
力状態の調査や調整（例えば作用圧力の均一化を図るた
めの調査や調整）に費やす作業や時間等を大幅に短縮で
き、又表面の仕上りが滑らかであるので仕上工程が必要
でなく製造時間の短縮化を図り得る。
［００２７］■請求項２によれば、製作期間が短くて済
むので、特に開発試験用の動翼を製造する場合に最適で
ある。
［００２８］■請求項１．２によれば、樹脂繊維（ファ
イバー）の不整現象をなくすことができるので、品質が
安定し向上する。
［００２９］■請求項１．２によれば、動翼の回転試験
に際しては、比強度及び比剛性高いために過回転試験が
高いレベルまで可能となり、又軽量化により動翼に発生
する負荷荷重を減少せしめることができて動翼に生ずる
応力を低減でき、更に過回転試験が高いレベルまで可能
となり、従って構造設計も容易となる。As explained above, according to the rotor blade and the method for manufacturing the rotor blade of the present invention, the following excellent effects can be achieved. [0024] ■ According to claim 1, the rotor blade body and the blade root are formed by laminating plate-shaped prepreg materials in which the resin fibers are oriented in the same direction, and a partition is provided at the center of the rotor blade body and the blade root. Since it is made by inserting plates, it is cheaper to manufacture and lighter than metal rotor blades, has high specific strength and specific rigidity, and has a smooth surface finish, which improves aerodynamic performance. [0025] ■ According to claim 1, it is possible to cope with various stresses such as tension, bending, torsion, and shearing that act on the rotor blade during use. [0026] ■ According to claim 2, in order to obtain the desired strength, investigation and adjustment of the working pressure state in the rotor blade body and the blade root during compression molding (for example, investigation to equalize the working pressure, The work and time required for adjustment can be greatly reduced, and since the surface finish is smooth, no finishing process is required, which can shorten manufacturing time. [0027] (2) According to claim 2, the manufacturing period is short, so it is particularly suitable for manufacturing rotor blades for development tests. [0028] ■According to claim 1.2, it is possible to eliminate the irregular phenomenon of resin fibers (fibers), thereby stabilizing and improving the quality. [0029] ■ According to claim 1.2, when testing the rotation of the rotor blade, the high specific strength and specific rigidity make it possible to perform an over-rotation test to a high level, and the weight reduction makes it possible to reduce the load generated on the rotor blade. This makes it possible to reduce the stress generated on the rotor blades, and also enables over-rotation testing to a high level, thereby facilitating structural design.
【図１】本発明の動翼を示す斜視図である。FIG. 1 is a perspective view showing a rotor blade of the present invention.
【図２】図１のＩＩ力方向ら見た図に相当し圧縮成形中
の状態を示す図である。FIG. 2 is a view corresponding to a view seen from the II force direction in FIG. 1 and showing a state during compression molding.
【図３】本発明の動翼の製造方法における積層状態を示
す斜視図である。FIG. 3 is a perspective view showing a stacked state in the method for manufacturing a rotor blade of the present invention.
１ 動翼本体
２ 翼根部
３ 仕切板
４、 ５．６ 板状のプリプレグ材４ａ、 ５ａ
、 ６ａ 樹脂繊維1 Moving blade body 2 Blade root 3 Partition plate 4, 5.6 Plate-shaped prepreg material 4a, 5a
, 6a resin fiber
【図１】[Figure 1]
Claims (2)
から成る動翼本体と、樹脂繊維の向きが動翼本体のプリ
プレグ材の樹脂繊維と同じ向きのプリプレグ材から成り
且つ動翼本体と連なる翼根部と、該翼根部の反動翼本体
側の略中央部から動翼本体に挿入した仕切板と、からな
ることを特徴とする動翼。Claim 1: A rotor blade body made of a prepreg material in which the resin fibers are oriented in the same direction; and a rotor blade body made of a prepreg material in which the resin fibers are oriented in the same direction as the resin fibers of the prepreg material of the rotor blade body, and connected to the rotor blade body. A rotor blade comprising: a blade root; and a partition plate inserted into the rotor blade body from approximately the center of the blade root on the reaction blade body side.
、板状のプリプレグ材をその樹脂繊維の向きを揃えて積
層形成し、翼根部の反動翼本体側の略中央部から仕切板
を、動翼本体に亘り適宜挿入し、ホットプレスにより圧
縮成形して一体化することを特徴とする動翼の製造方法
。[Claim 2] The rotor blade body and the blade root portion connected to the rotor blade body are formed by laminating plate-shaped prepreg materials with their resin fibers aligned in the same direction, and starting from the approximate center of the blade root portion on the reaction blade body side. A method for manufacturing a rotor blade, which comprises inserting a partition plate as appropriate across the rotor blade body and compression-molding it by hot pressing to integrate the partition plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP40975690A JPH04209901A (en) | 1990-12-10 | 1990-12-10 | Moving blade and manufacture thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP40975690A JPH04209901A (en) | 1990-12-10 | 1990-12-10 | Moving blade and manufacture thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH04209901A true JPH04209901A (en) | 1992-07-31 |
Family
ID=18519043
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP40975690A Pending JPH04209901A (en) | 1990-12-10 | 1990-12-10 | Moving blade and manufacture thereof |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH04209901A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5375978A (en) * | 1992-05-01 | 1994-12-27 | General Electric Company | Foreign object damage resistant composite blade and manufacture |
| US9945389B2 (en) | 2014-05-05 | 2018-04-17 | Horton, Inc. | Composite fan |
-
1990
- 1990-12-10 JP JP40975690A patent/JPH04209901A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5375978A (en) * | 1992-05-01 | 1994-12-27 | General Electric Company | Foreign object damage resistant composite blade and manufacture |
| US9945389B2 (en) | 2014-05-05 | 2018-04-17 | Horton, Inc. | Composite fan |
| US10415587B2 (en) | 2014-05-05 | 2019-09-17 | Horton, Inc. | Composite fan and method of manufacture |
| US10914314B2 (en) | 2014-05-05 | 2021-02-09 | Horton, Inc. | Modular fan assembly |
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