JP2966696B2 - Hollow wing - Google Patents
Hollow wingInfo
- Publication number
- JP2966696B2 JP2966696B2 JP17145893A JP17145893A JP2966696B2 JP 2966696 B2 JP2966696 B2 JP 2966696B2 JP 17145893 A JP17145893 A JP 17145893A JP 17145893 A JP17145893 A JP 17145893A JP 2966696 B2 JP2966696 B2 JP 2966696B2
- Authority
- JP
- Japan
- Prior art keywords
- core
- wing
- blade
- spacer
- outer plate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Description
【０００１】[0001]
【産業上の利用分野】本発明は、航空機等に使用される
ガスタービン原動機に適用される中空翼に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a hollow wing applied to a gas turbine engine used for an aircraft or the like.
【０００２】[0002]
【従来の技術】図７に、翼背側外板、翼背側コア、翼腹
側コアおよび翼腹側外板の４層からなり超塑性成形（Su
perplastic Forming, 以下ＳＰＦという）および拡散接
合（Diffusion Bonding 以下ＤＢという）で形成される
従来の中空翼の翼断面を示し、図７（Ａ）は成形前、図
７（Ｂ）はＳＰＦによる中空翼成形途中、図７（Ｃ）は
成形後を各々示す。これらの図において、１１はＳＰＦ
（第２工程）用の上型、２は下型、３，４はそれぞれ中
空翼を形成し、その内面に突起部２１が形成された外板
で、３は翼背側外板、４は翼腹側外板、５は翼前縁スペ
ーサ、６は翼後縁スペーサ、７，８は外板３，４の内側
にそれぞれ挿入され外板３，４の突起部２１にその外面
がＤＢにより各々接合されたコアで、７は翼背側コア、
８は翼腹側コアである。この様に中空翼は外板３，４お
よびコア７，８の４層で形成されており、従来は、図７
（Ａ）のＣ部詳細を示す図８に示される様に翼背側コア
７及び翼腹側コア８とも一定板厚のものが使用されてい
る。このため、ＳＰＦ後の中空翼の内部は図７（Ｃ）の
Ｄ部の詳細を示す図９に示される様にＳＰＦ時形状上応
力が大きくなるコア７，８の成形肩部２２に薄肉化が生
じ、この部分のコア７，８の板厚は成形前の１／４〜１
／５の板厚になることがある。この薄肉化は当然中空翼
の強度の低下を招き、設計値におけるガスタービンの使
用に支障が生じる不具合がある。2. Description of the Related Art FIG. 7 shows a superplastic forming (Su-form) comprising four layers of a wing back side skin, a wing back side core, a wing belly side core, and a wing belly side skin.
FIG. 7A shows a blade section of a conventional hollow blade formed by perplastic forming (hereinafter, referred to as SPF) and diffusion bonding (hereinafter, referred to as DB). FIG. During molding, FIG. 7C shows the state after molding. In these figures, 11 is the SPF
An upper plate for (second step), 2 is a lower die, 3 and 4 each form a hollow wing, and an outer plate having a projection 21 formed on its inner surface. Ventral outer skin 5, wing leading edge spacer, 6 wing trailing edge spacer, 7, 8 inserted inside outer plates 3, 4, respectively. Each of the joined cores, 7 is the wing back core,
8 is a wing ventral core. As described above, the hollow wing is formed by four layers of the outer plates 3 and 4 and the cores 7 and 8,
As shown in FIG. 8 showing the details of the portion C in FIG. 8A, both the blade back side core 7 and the blade side core 8 have a constant thickness. For this reason, the inside of the hollow blade after the SPF is reduced in thickness at the forming shoulders 22 of the cores 7 and 8 in which the stress increases in shape at the time of the SPF as shown in FIG. And the plate thickness of the cores 7 and 8 in this portion is 1/4 to 1 before molding.
/ 5 sheet thickness. This reduction in thickness naturally results in a decrease in the strength of the hollow blade, and there is a problem that the use of the gas turbine at the design value is hindered.
【０００３】[0003]
【発明が解決しようとする課題】本発明は、この様に外
板とコアの４層からなりＳＰＦ，ＤＢによって成形され
る中空翼において、中空部に挿入され中空翼を補強する
コアの成形肩部に局所的に形成されることのあるコアの
薄肉化を防止した中空翼を提供することを課題とする。SUMMARY OF THE INVENTION The present invention relates to a hollow blade formed of SPF and DB comprising four layers of an outer plate and a core as described above. It is an object to provide a hollow blade in which a core which may be locally formed in a portion is prevented from being thinned.
【０００４】[0004]
【課題を解決するための手段】このため、本発明の中空
翼は、それぞれの内面に突起部を形成したタービン翼を
形成する翼背側外板および翼腹側外板と、その外面が外
板の内面に断続的に設けられた突起部とＤＢされる接合
部近傍で、ＳＰＦ時形状上応力が大きくなる部分の内面
に、スペーサをＤＢによって接合したコアとで構成し、
外板とコアとを接合し、ＳＰＦで一体成形する手段とし
た。For this reason, the hollow blade of the present invention has a blade back side skin and a blade vent side skin which form a turbine blade having a projection formed on each inner surface, and the outer surface thereof has an outer surface. In the vicinity of a joint part which is provided intermittently on the inner surface of the plate and a DB, a core in which a spacer is joined by a DB to the inner surface of a portion where the stress increases in shape at the time of SPF,
A means for joining the outer plate and the core and integrally forming the same with SPF was used.
【０００５】[0005]
【作用】上述の手段により本発明の中空翼は、外板の内
面に接合され中空翼を補強するコアがＳＰＦ時、形状上
応力が大きくなる所のみスペーサ接合により板厚を増
し、応力が下げられるので局所的な薄肉化が防止され中
空翼の強度が損われることがなくなる。さらに、特に航
空機において重要な重量の増加が、強度の増加に比べて
小さく出来る利点もある。According to the above-mentioned means, the hollow wing of the present invention increases the plate thickness and reduces the stress by the spacer joint only at the point where the stress becomes large in shape when the core joined to the inner surface of the outer plate and reinforcing the hollow wing becomes SPF. As a result, local thinning is prevented, and the strength of the hollow blade is not impaired. Further, there is an advantage that the increase in weight, which is particularly important in an aircraft, can be made smaller than the increase in strength.
【０００６】[0006]
【実施例】以下、本発明の中空翼の実施例を図面により
説明する。図１ないし図６は本発明の一実施例を示す図
である。図１は、翼背側コア７と翼腹側コア８の間にコ
ア薄肉防止用のスペーサ９をはさんでＤＢする工程の説
明図である。図１（Ａ）はＤＢ前、図１（Ｂ）はＤＢ後
をそれぞれ示す。翼背側外板３の内面に形成された突起
部２１と翼背側コア７の外面及び翼腹側外板４の内面に
形成された突起部２１と翼腹側コア８の外面とは、各々
ＤＢ等で予備接合しておく。なお、外板の内面の突起部
２１は、あらかじめケミカルミリング等で形成されてい
る。予備接合されて一体化された翼背側コア外板３、翼
背側コア７と翼腹側外板４、翼腹側コア８との間、即ち
コアの内面側に翼前縁スペーサ５、複数のコア薄肉防止
用のスペーサ９及び翼後縁スペーサ６をはさみ込んだ翼
構成部品を、図１（Ａ）に示すように上型１と下型２の
間に組込む。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiments of the hollow wing of the present invention will be described below with reference to the drawings. 1 to 6 are views showing an embodiment of the present invention. FIG. 1 is an explanatory diagram of a step of performing DB by sandwiching a spacer 9 for preventing core thinning between a wing back side core 7 and a wing abdominal side core 8. 1A shows the state before the DB, and FIG. 1B shows the state after the DB. The protrusion 21 formed on the inner surface of the wing back side outer plate 3, the outer surface of the wing back side core 7, the protrusion 21 formed on the inner surface of the wing ventral outer plate 4, and the outer surface of the wing ventral core 8 are: Each is pre-joined by a DB or the like. The protrusion 21 on the inner surface of the outer plate is formed in advance by chemical milling or the like. The blade back side core skin 3, which is pre-joined and integrated, between the blade back side core 7 and the blade front side skin 4, and the blade front side core 8, that is, on the inner surface side of the core, the blade front edge spacer 5, A blade component including a plurality of core thin-wall preventing spacers 9 and a blade trailing edge spacer 6 is assembled between the upper die 1 and the lower die 2 as shown in FIG.
【０００７】コア薄肉防止用のスペーサ９は、図１
（Ａ）のＡ部を詳細に示す図２に示されるように、翼背
側外板３の内面に形成された突起部２１と翼背側コア７
の外面との予備接合部の翼背側コア７の内面（翼背側コ
ア７と翼腹側コア８との間）、および翼腹側外板４の内
面に形成された突起部２１と翼腹側コアの外面との予備
接合部の翼腹側コア８の内面（翼腹側コア８と翼背側コ
ア７との間）にそれぞれはさみ込まれる。また、スペー
サ９は図３、および図４に示す形状のものが使用され。
図３に示すものは、翼背側外板３、翼腹側外板４のそれ
ぞれの外板の内面に形成される突起部２１が円形に形成
され外板内面に島状に配置されて、ＳＰＦ後コアを凹凸
のディンプル形状にする場合に好適なスペーサ９ａであ
る。[0007] The spacer 9 for preventing the core from being thin is shown in FIG.
As shown in FIG. 2 showing the portion A of FIG. 2A in detail, the protrusion 21 formed on the inner surface of the wing back side outer plate 3 and the wing back side core 7 are shown.
The inner surface of the wing-backside core 7 (between the wing-backside core 7 and the wing-ventral core 8) at the pre-joined portion with the outer surface of the wing, and the projection 21 and the wing formed on the inner surface of the wing-ventral outer plate 4 The inner surface of the wing abdominal core 8 (between the wing abdominal core 8 and the wing aft core 7) is preliminarily joined to the outer surface of the abdominal core. Further, the spacer 9 having the shape shown in FIGS. 3 and 4 is used.
In FIG. 3, the protrusions 21 formed on the inner surface of each of the wing back side outer plate 3 and the wing ventral side outer plate 4 are formed in a circular shape and arranged in an island shape on the inner surface of the outer plate. It is a spacer 9a suitable when the core after the SPF is formed into a dimple shape with irregularities.
【０００８】さらに、図４に示すものは、翼外板の内面
に形成される突起部２１が翼根部かさ翼先端方向へ直
線、折線、曲線的に島状に配置されてＳＰＦ成形後、コ
アを直線、折線、曲線的な波状にする場合に好適なスペ
ーサ９ｂである。スペーサ９ａ，９ｂ共その外周又は両
端は、先細形状となっており、コア７，８の内面にはさ
み込まれてＤＢされる時に、ボイドが残らない効果を有
している。Further, FIG. 4 shows that the protrusions 21 formed on the inner surface of the wing outer plate are linearly, brokenly and curvedly arranged in the shape of an island in the direction of the root of the blade or the tip of the blade. Is a spacer 9b suitable for forming a straight line, a broken line, or a curved wave shape. Both the outer periphery or both ends of the spacers 9a and 9b have a tapered shape, and have an effect that voids do not remain when the spacers 9a and 9b are inserted into the inner surfaces of the cores 7 and 8 and subjected to DB.
【０００９】図１（Ａ）に示される様にスペーサ９を上
型１と下型２の間組込んだ後、上型、下型をＤＢ温度ま
で加熱し、翼背側コア７と翼腹側コア８の間を真空引
き、翼背側外板３と翼背側コア７の間及び翼腹側外板４
と翼腹側コア８の間にＡｒガス等の不活性ガスで注入し
て加圧する事により、翼背側コア７、コア薄肉防止用の
スペーサ９及び翼腹側コア８がＤＢにより一体化でき
る。ＤＢ後は、図１（Ｂ）に示すようにコア薄肉防止用
のスペーサ９をはさみ込んだ所のコア（１０）は板厚が
局部的に厚くなる。図５は、図１（Ｂ）に示すコアと外
板との一体化した成形品をＳＰＦにより翼形に膨らませ
成形する説明図である。ＳＰＦ（第２工程）用の上型１
１と下型２の空間は、翼前後縁部に当たる所以外翼形形
状を成形されており、図１（Ｂ）の成形品をその空間に
組込んで、上型および下型をＳＰＦ温度まで加熱し、翼
背側外板３とコア１０の間およびコア１０と翼腹側外板
４の間にＡｒガス等の不活性ガスを注入して加圧する事
により、図５（Ａ），図５（Ｂ），図５（Ｃ）の順に示
す様に、翼背側外板３、コア１０、翼腹側外板４が一体
となって中空翼が成形される。図６は、５図５（ｃ）の
Ｂ部詳細を示す図であり、外面が外板の内面の突起部に
接合される、コアの内面にスペーサ９を入れることによ
り、この部分を局所的に厚くされたコア１０は、成形
後、成形時に形状上応力が集中する成形肩部に薄肉化を
生じず、中空翼は設計値通りの強度を保持する。As shown in FIG. 1 (A), after assembling the spacer 9 between the upper die 1 and the lower die 2, the upper die and the lower die are heated to the DB temperature, and the blade back core 7 and the blade ventral side. The space between the cores 8 is evacuated, and the space between the blade back side skin 3 and the blade back side core 7 and between the blade back side skin 4
By injecting and pressurizing with an inert gas such as Ar gas between the airfoil and the airfoil core 8, the airfoil back core 7, the spacer 9 for preventing core thinning, and the airfoil core 8 can be integrated by DB. . After DB, as shown in FIG. 1B, the core (10) where the spacer 9 for preventing the core thinning is inserted is locally thickened. FIG. 5 is an explanatory diagram in which an integrated product of the core and the outer plate shown in FIG. Upper mold 1 for SPF (2nd process)
The space between the lower mold 1 and the lower mold 2 is formed in an airfoil shape except for the area corresponding to the front and rear edges of the wing. The molded product shown in FIG. By heating and injecting and pressurizing an inert gas such as Ar gas between the wing back side skin 3 and the core 10 and between the core 10 and the wing belly side skin 4, FIG. As shown in the order of FIG. 5B and FIG. 5C, a hollow blade is formed by integrating the blade back side outer plate 3, the core 10, and the blade front side outer plate 4. FIG. 6 is a view showing the details of the portion B in FIG. 5 (c). The outer surface is joined to the protrusion on the inner surface of the outer plate. After the core 10 is thickened, the molding blade does not become thinner at the molding shoulder where the stress is concentrated on the shape at the time of molding, and the hollow blade maintains the strength as designed.
【００１０】[0010]
【発明の効果】上述したように、本発明の中空翼は特許
請求範囲に示す構成により、タービン翼を形成する外板
の内部に挿入、接合されて外板を補強するコアにＳＰＦ
時に形状上生じていた成形肩部の薄肉部が形成されず、
一様な厚みのものとすることができるため、タービン翼
の剛性向上、耐振動性向上および耐異物衝突性の向上を
図ることができる。さらに、コアの一部分のみにスペー
サを接合することにより、重量の増加を小さくすること
ができエンジンの重量軽減を資することができる。As described above, the hollow blade according to the present invention has an SPF which is inserted and joined inside the outer plate forming the turbine blade to reinforce the outer plate by the structure shown in the claims.
Sometimes the thin portion of the molding shoulder that was generated on the shape is not formed,
Since the thickness can be uniform, the turbine blade can be improved in rigidity, vibration resistance, and foreign object collision resistance. Furthermore, by joining the spacer to only a part of the core, the increase in weight can be reduced and the weight of the engine can be reduced.
【図１】本発明の中空翼の成型の第１工程であるＤＢ工
程を説明するための図で、図１（Ａ）ＤＢ前を示す断面
図、図１（Ｂ）はＤＢ後を示す断面図。FIG. 1 is a view for explaining a DB step which is a first step of molding a hollow blade according to the present invention, and FIG. 1 (A) is a sectional view showing a state before DB, and FIG. 1 (B) is a sectional view showing a state after DB. FIG.
【図２】図１（Ａ）のＡ部詳細を示す断面図。FIG. 2 is a sectional view showing details of a portion A in FIG. 1 (A).
【図３】本発明の中空翼に使用されるスペーサの第一実
施例を示す図で、図３（Ａ）は側面図、図３（Ｂ）は平
面図。3A and 3B are diagrams showing a first embodiment of a spacer used for a hollow blade according to the present invention, wherein FIG. 3A is a side view and FIG. 3B is a plan view.
【図４】本発明の中空翼に使用されるスペーサの第２実
施例を示す図で、図４（Ａ）は断面図、図４（Ｂ）は平
面部分図。FIG. 4 is a view showing a second embodiment of the spacer used for the hollow blade of the present invention, wherein FIG. 4 (A) is a sectional view and FIG. 4 (B) is a partial plan view.
【図５】本発明の中空翼の成型の第２工程であるＳＰＦ
工程を説明するための図で、図５（Ａ）はＳＰＦ前を示
す断面図、図５（Ｂ）はＳＰＦ途中を示す断面図、図５
（Ｃ）はＳＰＦ後を示す断面図。FIG. 5 is a second step of molding the hollow wing of the present invention, SPF.
5A is a cross-sectional view showing the state before the SPF, FIG. 5B is a cross-sectional view showing the middle of the SPF, FIG.
(C) is a sectional view showing the state after the SPF.
【図６】図５（Ｃ）のＢ部詳細を示す断面図である。FIG. 6 is a sectional view showing details of a portion B in FIG. 5 (C).
【図７】従来の中空翼の成型の第２工程であるＳＰＦ工
程を説明するための図で、図７（Ａ）はＳＰＦ前を示す
断面図、図７（Ｂ）はＳＰＦ途中を示す図、図７（Ｃ）
はＳＰＦ後を示す断面図。7A and 7B are views for explaining an SPF step which is a second step of the conventional hollow blade molding. FIG. 7A is a cross-sectional view showing a state before the SPF, and FIG. , FIG. 7 (C)
FIG. 3 is a cross-sectional view showing a state after the SPF.
【図８】図７（Ａ）のＣ部詳細を示す断面図。FIG. 8 is a sectional view showing details of a portion C in FIG. 7 (A).
【図９】図７（Ｃ）のＤ部詳細を示す断面図である。FIG. 9 is a cross-sectional view showing details of a portion D in FIG. 7 (C).
１ 上型（第１工程用） ２ 下型 ３ 突起部付翼背側外板 ４ 突起部付翼腹側外板 ５ 翼前縁スペーサ ６ 翼後縁スペーサ ７ 翼背側コア ８ 翼腹側コア ９ コア薄肉防止スペーサ ９ａ コア薄肉防止スペーサ（凹凸ディンプル
コア用） ９ｂ コア薄肉防止スペーサ（波状コア用） １０， ７，８，９がＤＢ後一体化したコア １１ 上型（第２工程用） ２１ 外板内面の突起部 ２２，２３ コア成形肩部DESCRIPTION OF SYMBOLS 1 Upper die (for 1st process) 2 Lower die 3 Blade back side skin with projection 4 Blade front side skin with projection 5 Blade leading edge spacer 6 Blade trailing edge spacer 7 Blade back side core 8 Blade back side core Reference Signs List 9 core thin prevention spacer 9a core thin prevention spacer (for uneven dimple core) 9b core thin prevention spacer (for wavy core) 10, 7, 8, 9 are integrated after DB 11 Upper die (for second step) 21 Projection on inner surface of outer plate 22, 23 Core molding shoulder
Claims (1)
部を形成して、前記中空部にコアを挿入、結合して形成
される中空翼において、前記コアの内面に断続的に配設
されたスペーサを有し、前記スペーサと前記コアおよび
該スペーサが配設されたコアの外面と前記外板の内面に
形成された突起部をそれぞれ拡散接合し、前記スペーサ
が一体化された前記コアと前記外板とを超塑性成形して
中空の翼型に成形したことを特徴とする中空翼。1. A hollow blade formed by forming a hollow portion inside an outer plate forming a turbine blade and inserting and connecting a core into the hollow portion, and intermittently disposed on an inner surface of the core. The core integrated with the spacer, the outer surface of the core having the spacer and the core and the protrusion formed on the inner surface of the outer plate are diffusion-bonded to each other, and the spacer is integrated. And a hollow blade formed by superplastically forming the outer plate and the outer plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17145893A JP2966696B2 (en) | 1993-07-12 | 1993-07-12 | Hollow wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17145893A JP2966696B2 (en) | 1993-07-12 | 1993-07-12 | Hollow wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0726902A JPH0726902A (en) | 1995-01-27 |
| JP2966696B2 true JP2966696B2 (en) | 1999-10-25 |
Family
ID=15923484
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP17145893A Expired - Fee Related JP2966696B2 (en) | 1993-07-12 | 1993-07-12 | Hollow wing |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2966696B2 (en) |
-
1993
- 1993-07-12 JP JP17145893A patent/JP2966696B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0726902A (en) | 1995-01-27 |
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| Date | Code | Title | Description |
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| A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 19990713 |
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| LAPS | Cancellation because of no payment of annual fees |