JP3684620B2 - Interblade spacer seal structure - Google Patents

Interblade spacer seal structure Download PDF

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Publication number
JP3684620B2
JP3684620B2 JP17547895A JP17547895A JP3684620B2 JP 3684620 B2 JP3684620 B2 JP 3684620B2 JP 17547895 A JP17547895 A JP 17547895A JP 17547895 A JP17547895 A JP 17547895A JP 3684620 B2 JP3684620 B2 JP 3684620B2
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Japan
Prior art keywords
blade
spacer
seal
contact
seal member
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JP17547895A
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JPH094410A (en
Inventor
広之 山本
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石川島播磨重工業株式会社
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Description

【０００１】
【産業上の利用分野】
この発明は、翼と翼との間に設けられて流れを円滑にする翼間スペーサと各翼表面と間をシールするシール構造に関し、シール部材が剥がれずに完全にシールできるようにしたもので、特に航空用エンジンなどのファンに好適なものである。
【０００２】
【従来の技術】
航空用や産業用などのガスタービンの圧縮機では、入口部分に軸の外周に複数の翼を取付けて構成されたファンが設けられており、例えば図２および図３に示すように、軸のディスク１の外周に複数のブレード（翼）２が取付けられるとともに、各ブレード２の内周側である基端部間に後段に空気を円滑に流すためのスペーサ３が配置され、前後の固定リング４，５を介して軸のディスク１に固定されている。
【０００３】
このようなスペーサ３とブレード２との間に隙間が形成されると、ファンに流入する空気の一部が漏れて循環するクリアランス流が生じるなどの問題があり、圧縮機の性能低下を招いてしまう。
【０００４】
そこで、スペーサ３とブレード２との間にシール部材としてシールラバー６を介在させてシールすることが行われている。
【０００５】
このシールラバー６を用いるシール構造では、図４に示すように、スペーサ３の円周方向両側に軸方向両端部を除いてブレード２と対向する部分に側方に開口したシール部材取付溝７を形成し、このシール部材取付溝７にファンの外周面である上面に接着部６ａが形成され、外側下部にシール用のリップ部６ｂが形成されたシールラバー６を装着し、接着部６ａを接着剤で取付けて固定するようにしている。
【０００６】
そして、シールラバー６のブレード２と接触しないファンの先端部Ａでは、ブレード２を挾むシールラバー６同志のリップ部６ｂを接触させてシールするとともに、これより後方のブレード２と接触する先端部Ｂ及びこれ以降の部分Ｃでは、リップ部６ｂをブレード２の表面に押し付けて変形させて接触させてシールするようにしている。
【０００７】
このようなシール構造では、シール性の向上のために大きな押圧接触力を確保する必要があることから、シールラバー６のブレード２と接触しない先端部Ａ及びこれより後方のブレード２と接触する先端部Ｂの接触部の内側に補強用繊維６ｃを埋設するとともに、リップ部６ｂの下部内側にも補強用繊維６ｃを埋設するようにし、さらにシールラバー６のブレード２と接触する先端部Ｂ以降の部分Ｃには、図４（ａ）中に示すように、内部全体に補強用繊維６ｃが埋設してある。
【０００８】
【発明が解決しようとする課題】
ところが、このようなシールラバー６を用いるシール構造では、ブレード２にシールラバー６を接触させると、リップ部６ｂに大きな変形が生じ、この変形によってシールラバー６をスペーサ３に接着している先端部Ａ，Ｂの接着部６ａも変形し、シールラバー６が剥がれてしまい、空気の漏れが生じてしまうという問題がある。
【０００９】
この発明はかかる従来技術の問題点に鑑みてなされたもので、シール部材が剥がれること無く、空気の漏れをシールすることができる翼間スペーサのシール構造を提供しようとするものである。
【００１０】
【課題を解決するための手段】
上記問題点を解決するためこの発明の翼間スペーサのシール構造は、軸外周に取付けられる複数の翼の基端部間に設けられるスペーサと各翼との間をシールするシール構造であって、前記スペーサの翼との対向面にシール部材取付溝を形成する一方、このシール部材取付溝の内周面に外周側接着部を介して接着されるシール部材を、翼面に押圧接触されるリップ部の変形力の前記外周側接着部への伝達を緩和してシールできる剛性とするとともに、前記外周接着部と前記リップ部との間に変形力の伝達を緩和する凹部を形成し、翼面と接触しない前記シール部材のリップ部同志が接触する形状に形成してなることを特徴とするものである。
【００１１】
【作用】
この翼間スペーサのシール構造によれば、軸外周に取付けられる複数の翼の基端部間に設けられるスペーサの翼との対向面にシール部材取付溝を形成し、このシール部材取付溝の内周面に外周側接着部を介して接着されるシール部材の剛性と形状を、翼面に押圧接触されるリップ部の変形力が接着部へ伝達されるのを緩和できるように形成しており、シール性を確保しながら接着部が剥がれないようにしている。
【００１２】
【実施例】
以下、この発明の一実施例を図面に基づき詳細に説明する。
図１はこの発明の翼間スペーサのシール構造の一実施例にかかり、（ａ）は外観斜視図、（ｂ）はブレード（翼）と接触しない先端部の正面図、（ｃ）はブレード（翼）と接触する先端部の横断面図である。
【００１３】
この翼間スペーサのシール構造１０では、既に図２〜図４で説明したシール構造とシール部材としてのシールラバー１１の構成が異なるものであり、軸のディスク１に取付けられるブレード２、スペーサ３および固定リング４，５の構成は同一である。
【００１４】
この翼間スペーサのシール構造１０で使用されるシールラバー１１は、ブレード（翼）２と接触する先端部Ｂおよびそれ以降の部分Ｃの上面（ファン中心に対する外周面）にシール部材取付溝７への接着部１１ａが平坦に形成され、接着剤で固定できるようになっている。そして、このシールラバー１１のシール部材取付溝７側と反対側のブレード２と接触する側の下側（ファンに対する内周側）には、断面が略三角形状とされて突き出したリップ部１１ｂが形成されており、ブレード２と接触しない先端部Ａはブレード２を挾む両側のシールラバー１１，１１のリップ部１１ｂ同志が接触してシールできるように形成され、ブレード２と接触する先端部Ｂおよびそれ以降の部分Ｃはブレード２の表面に押し付けてシールできるように形成してある。
【００１５】
このようなシールラバー１１では、その剛性および形状を最適にすることで、リップ部１１ｂをブレード２に押し当た場合の変形による力が接着部１１ａに及ばないように変形力の伝達を緩和できるようにしている。
【００１６】
このため、シールラバー１１のブレード２と接触しない先端部Ａには、接着部１１ａとリップ部１１ｂとの間の部分に凹部１１ｃを形成し、リップ部１１ｂがブレード２に接触して変形された場合の変形力の接着部１１ａへの伝達を緩和できる形状としてある。
【００１７】
また、シールラバー１１のブレード２と接触しない先端部Ａ及びブレード２と接触する先端部Ｂには、リップ部１１ｂを補強するための補強用繊維１１ｄの埋設がブレード２との接触部内側のみとされてリップ部１１ｂの剛性を凹部１１ｃの形状効果と併せて小さくするようにしてある。
【００１８】
さらに、シールラバー１１のブレード２と接触する部分Ｃには、周囲全体に補強用繊維１１ｄが埋設されており、この部分では大きな押圧接触力を確保できるようにしてある。
【００１９】
このようなシールラバー１１を用いた翼間スペーサのシール構造１０では、スペーサ３の円周方向両側に軸方向両端部を除いてブレード２と対向する部分の側方に開口して形成したシール部材取付溝７にシールラバー１１を装着し、シールラバー１１の上面の接着部１１ａを接着剤で取付けて固定して構成される。
【００２０】
この翼間スペーサのシール構造１０では、シールラバー１１のブレード２と接触しない先端部Ａおよびこれに続くブレード２と接触する先端部Ｂの接着部１１ａとリップ部１１ｂとの間の形状として凹部１１ｃが形成されるとともに、リップ部１１ｂの剛性が補強用繊維１１ｄの埋設量の減少によって小さくしてあり、図１（ｃ）に示すように、シールラバー１１のブレード２と接する先端部Ｂでリップ部１１ｂが大きく変形して大きな押圧接触力が得られる状態でも、その変形力が上面（ファンに対する外周面）の接着部１１ａに及ぶことが緩和され、接着剤の剥離が防止される。
【００２１】
これにより、ファンの先端から吸い込まれる空気がシールラバー１１の先端部Ａの隙間から漏れることがなく、クリアランス流を防止して圧縮機の性能向上を図ることができる。
【００２２】
また、シールラバー１１の先端部Ｂ以降の部分Ｃは、これまでと同様に補強用繊維１１ｄが周囲全体に埋設してあるので、大きな押圧接触力を得ることができ、シール性を維持することができる。
【００２３】
なお、上記実施例では、翼間のスペーサのシール構造を航空用エンジンのファン部分に適用する場合で説明したが、これに限らず、翼の間にスペーサを配置してシールする場合のあるシール構造として広く適用することができる。
【００２４】
また、シール部材の形状及び剛性については、リップ部の変形の影響が接着部に伝達されることを緩和できる凹部の形成と補強材の埋設量の調整で行うようにすれば良い。
【００２５】
【発明の効果】
以上、一実施例とともに具体的に説明したようにこの発明の翼間スペーサのシール構造によれば、軸外周に取付けられる複数の翼の基端部間に設けられるスペーサの翼との対向面にシール部材取付溝を形成し、このシール部材取付溝の内周面に外周側接着部を介して接着されるシール部材の剛性と形状を、翼面に押圧接触されるリップ部の変形力が接着部へ伝達されるのを緩和できるように形成したので、シール性を確保しながら接着部が剥がれないようにすることができ、空気の漏れを無くして性能向上を図ることができる。
【００２６】
これにより、航空用エンジンなどの圧縮機では、クリアランス流を防止して性能向上を図ることができる。
【図面の簡単な説明】
【図１】この発明の翼間スペーサのシール構造の一実施例にかかり、（ａ）は外観斜視図、（ｂ）はブレード（翼）と接触しない先端部の正面図、（ｃ）はブレード（翼）と接触する先端部の横断面図である。
【図２】この発明の翼間スペーサのシール構造が適用される航空用エンジンのファンの部分斜視図である。
【図３】この発明の翼間スペーサのシール構造が適用される航空用エンジンのファンの部分縦断面図である。
【図４】従来の翼間スペーサのシール構造にかかり、（ａ）は外観斜視図、（ｂ）はブレード（翼）と接触しない先端部の正面図、（ｃ）はブレード（翼）と接触する先端部の横断面図である。
【符号の説明】
１ 軸のディスク
２ ブレード（翼）
３ スペーサ
４，５ 固定リング
１０ 翼間スペーサのシール構造
１１ シールラバー（シール部材）
１１ａ 接着部
１１ｂ リップ部
１１ｃ 凹部
１１ｄ 補強用繊維
Ａ シール部材のブレードと接触しない先端部
Ｂ シール部材のブレードと接触する先端部
Ｃ シール部材のブレードと接触する部分[0001]
[Industrial application fields]
The present invention relates to a seal structure that is provided between blades and seals between the blade surfaces that smooth the flow and the surfaces of the blades, so that the seal member can be completely sealed without peeling off. Especially, it is suitable for a fan such as an aircraft engine.
[0002]
[Prior art]
2. Description of the Related Art Gas turbine compressors for aviation and industrial use are provided with a fan having a plurality of blades attached to the outer periphery of the shaft at the inlet portion. For example, as shown in FIGS. A plurality of blades (blades) 2 are attached to the outer periphery of the disk 1, and a spacer 3 for smoothly flowing air downstream is disposed between the base end portions on the inner peripheral side of each blade 2, and the front and rear fixing rings 4 and 5 are fixed to the disk 1 of the shaft.
[0003]
If such a gap is formed between the spacer 3 and the blade 2, there is a problem that a part of the air flowing into the fan leaks and circulates, which causes a reduction in the performance of the compressor. End up.
[0004]
Therefore, sealing is performed by interposing a seal rubber 6 as a seal member between the spacer 3 and the blade 2.
[0005]
In the seal structure using this seal rubber 6, as shown in FIG. 4, seal member mounting grooves 7 opened laterally are formed on portions facing the blade 2 except for both axial ends on both sides in the circumferential direction of the spacer 3. Then, the seal member mounting groove 7 is attached with a seal rubber 6 having an adhesive portion 6a formed on the upper surface, which is the outer peripheral surface of the fan, and a seal lip portion 6b formed on the outer lower portion, and the adhesive portion 6a is bonded. It is attached and fixed with an agent.
[0006]
Then, at the tip A of the fan that does not contact the blade 2 of the seal rubber 6, the lip 6b of the seal rubber 6 sandwiching the blade 2 is brought into contact and sealed, and the tip that contacts the blade 2 behind this is sealed. In B and the subsequent portion C, the lip portion 6b is pressed against the surface of the blade 2 to be deformed and brought into contact for sealing.
[0007]
In such a seal structure, since it is necessary to ensure a large pressing contact force in order to improve the sealing performance, the tip portion A that does not contact the blade 2 of the seal rubber 6 and the tip that contacts the blade 2 behind it. The reinforcing fiber 6c is embedded inside the contact part of the part B, and the reinforcing fiber 6c is embedded also inside the lower part of the lip part 6b. In part C, as shown in FIG. 4A, reinforcing fibers 6c are embedded in the entire interior.
[0008]
[Problems to be solved by the invention]
However, in such a seal structure using the seal rubber 6, when the seal rubber 6 is brought into contact with the blade 2, a large deformation occurs in the lip portion 6 b, and this deformation causes the tip portion that adheres the seal rubber 6 to the spacer 3. There is also a problem that the adhesive portions 6a of A and B are also deformed, the seal rubber 6 is peeled off, and air leaks.
[0009]
The present invention has been made in view of such problems of the prior art, and an object of the present invention is to provide a sealing structure for an interblade spacer capable of sealing air leakage without peeling off a sealing member.
[0010]
[Means for Solving the Problems]
In order to solve the above problems, the interblade spacer seal structure of the present invention is a seal structure that seals between each blade and a spacer provided between the base ends of a plurality of vanes attached to the outer periphery of the shaft, The seal member mounting groove is formed on the surface of the spacer facing the blade, and the seal member bonded to the inner peripheral surface of the seal member mounting groove via the outer peripheral side adhesive portion is pressed against the blade surface. The rigidity of the blade is reduced by reducing the transmission of the deformation force of the part to the outer peripheral side adhesive part, and a recess is formed between the outer peripheral adhesive part and the lip part to reduce the transmission of the deformation force. The lip portions of the seal member that do not come into contact with each other are formed in a shape in contact with each other.
[0011]
[Action]
According to the seal structure of the inter-blade spacer, the seal member mounting groove is formed on the surface facing the blade of the spacer provided between the base ends of the plurality of blades mounted on the outer periphery of the shaft. The rigidity and shape of the sealing member that is bonded to the peripheral surface via the outer peripheral adhesive portion is formed so that the deformation force of the lip portion that is pressed against the blade surface can be reduced from being transmitted to the adhesive portion. In addition, the adhesive portion is prevented from peeling off while ensuring the sealing property.
[0012]
【Example】
Hereinafter, an embodiment of the present invention will be described in detail with reference to the drawings.
1A and 1B show an embodiment of a sealing structure for an inter-blade spacer according to the present invention, in which FIG. 1A is an external perspective view, FIG. 1B is a front view of a tip portion not in contact with a blade (blade), and FIG. It is a cross-sectional view of the front-end | tip part which contacts a wing | blade).
[0013]
The interblade spacer seal structure 10 is different from the seal structure already described with reference to FIGS. 2 to 4 in the configuration of the seal rubber 11 as a seal member. The blade 2, the spacer 3 attached to the shaft disk 1, The structures of the fixing rings 4 and 5 are the same.
[0014]
The seal rubber 11 used in the interblade spacer seal structure 10 is connected to the seal member mounting groove 7 on the upper surface (the outer peripheral surface with respect to the center of the fan) of the tip B and the subsequent part C in contact with the blade (blade) 2. The adhesive portion 11a is formed flat and can be fixed with an adhesive. And on the lower side (inner peripheral side with respect to the fan) of the seal rubber 11 on the side opposite to the seal member mounting groove 7 side, the lip portion 11b protruding in a substantially triangular shape is projected. The tip A that is formed and not in contact with the blade 2 is formed so that the lip portions 11b of the seal rubbers 11 and 11 on both sides of the blade 2 can be in contact with each other and sealed, and the tip B that is in contact with the blade 2 And the subsequent portion C is formed so as to be pressed against the surface of the blade 2 and sealed.
[0015]
In such a seal rubber 11, by optimizing its rigidity and shape, the transmission of the deformation force can be reduced so that the force due to the deformation when the lip portion 11b is pressed against the blade 2 does not reach the bonding portion 11a. I am doing so.
[0016]
For this reason, a concave portion 11c is formed in a portion between the adhesive portion 11a and the lip portion 11b at the tip end portion A that does not contact the blade 2 of the seal rubber 11, and the lip portion 11b is deformed by contacting the blade 2. In this case, the shape can be relieved of transmission of the deforming force to the bonding portion 11a.
[0017]
Further, in the tip end portion A that does not contact the blade 2 of the seal rubber 11 and the tip end portion B that contacts the blade 2, the embedment of reinforcing fibers 11d for reinforcing the lip portion 11b is only inside the contact portion with the blade 2. Thus, the rigidity of the lip portion 11b is reduced together with the shape effect of the concave portion 11c.
[0018]
Further, in the portion C of the seal rubber 11 that comes into contact with the blade 2, reinforcing fibers 11d are embedded in the entire periphery, and a large pressing contact force can be secured in this portion.
[0019]
In the seal structure 10 of the interblade spacer using the seal rubber 11 as described above, a seal member formed by opening on the both sides in the circumferential direction of the spacer 3 on the side facing the blade 2 except for both axial ends. A seal rubber 11 is mounted in the mounting groove 7, and an adhesive portion 11a on the upper surface of the seal rubber 11 is attached and fixed with an adhesive.
[0020]
In this interblade spacer seal structure 10, a recess 11 c is formed as a shape between the tip portion A of the seal rubber 11 that does not come into contact with the blade 2 and the adhesive portion 11 a and the lip portion 11 b of the tip portion B that comes into contact with the blade 2. Is formed, and the rigidity of the lip portion 11b is reduced by the reduction of the amount of the reinforcing fiber 11d embedded, and the lip is formed at the tip B contacting the blade 2 of the seal rubber 11 as shown in FIG. Even in a state where the portion 11b is greatly deformed and a large pressing contact force is obtained, the deformation force is eased to reach the adhesive portion 11a on the upper surface (the outer peripheral surface with respect to the fan), and peeling of the adhesive is prevented.
[0021]
Thereby, the air sucked from the front end of the fan does not leak from the gap at the front end portion A of the seal rubber 11, and the flow of the clearance can be prevented to improve the performance of the compressor.
[0022]
In addition, since the reinforcing fiber 11d is embedded in the entire periphery of the portion C after the distal end B of the seal rubber 11 as before, a large pressing contact force can be obtained and the sealing performance can be maintained. Can do.
[0023]
In the above embodiments, the spacer seal structure between the wings has been described as applied to the fan portion of the aircraft engine. However, the present invention is not limited to this, and there is a seal that may be sealed by placing a spacer between the wings. Can be widely applied as a structure.
[0024]
Further, the shape and rigidity of the seal member may be determined by forming a recess that can alleviate the effect of the deformation of the lip portion being transmitted to the bonding portion and adjusting the amount of reinforcement embedded.
[0025]
【The invention's effect】
As described above in detail with reference to one embodiment, according to the seal structure of the interblade spacer of the present invention, on the surface facing the wing of the spacer provided between the base ends of the plurality of wings attached to the outer periphery of the shaft. The seal member mounting groove is formed, and the rigidity and shape of the seal member that is bonded to the inner peripheral surface of the seal member mounting groove via the outer peripheral side bonding portion is bonded to the deformation force of the lip portion that is pressed against the blade surface. Since it is formed so that transmission to the part can be relaxed, it is possible to prevent the adhesive part from peeling off while ensuring sealing performance, and it is possible to improve performance by eliminating air leakage.
[0026]
Thereby, in compressors, such as an aircraft engine, a clearance flow can be prevented and performance improvement can be aimed at.
[Brief description of the drawings]
1A and 1B show an embodiment of a seal structure for an inter-blade spacer according to the present invention, in which FIG. 1A is an external perspective view, FIG. It is a cross-sectional view of the front-end | tip part which contacts (wing | blade).
FIG. 2 is a partial perspective view of a fan of an aircraft engine to which the interblade spacer seal structure of the present invention is applied.
FIG. 3 is a partial longitudinal sectional view of a fan of an aircraft engine to which the interblade spacer seal structure of the present invention is applied.
4A is a perspective view of an external appearance, FIG. 4B is a front view of a tip portion not in contact with a blade, and FIG. 4C is in contact with the blade. It is a cross-sectional view of the tip part.
[Explanation of symbols]
1 axis disk 2 blade (wing)
3 Spacer 4, 5 Fixing ring 10 Seal structure of inter-blade spacer 11 Seal rubber (seal member)
11a Adhesive part 11b Lip part 11c Recessed part 11d Reinforcing fiber A Tip part B that does not contact the blade of the seal member Tip part C that contacts the blade of the seal member Part that contacts the blade of the seal member

Claims (1)

軸外周に取付けられる複数の翼の基端部間に設けられるスペーサと各翼との間をシールするシール構造であって、前記スペーサの翼との対向面にシール部材取付溝を形成する一方、このシール部材取付溝の内周面に外周側接着部を介して接着されるシール部材を、翼面に押圧接触されるリップ部の変形力の前記外周側接着部への伝達を緩和してシールできる剛性とするとともに、前記外周接着部と前記リップ部との間に変形力の伝達を緩和する凹部を形成し、翼面と接触しない前記シール部材のリップ部同志が接触する形状に形成してなることを特徴とする翼間スペーサのシール構造。A seal structure that seals between each blade and a spacer provided between the base ends of a plurality of blades attached to the outer periphery of the shaft, wherein a seal member attachment groove is formed on a surface facing the blade of the spacer, A seal member that is bonded to the inner peripheral surface of the seal member mounting groove via an outer peripheral side adhesive portion is sealed by reducing the transmission of the deforming force of the lip portion pressed against the blade surface to the outer peripheral side adhesive portion. A recess that relaxes transmission of deformation force is formed between the outer peripheral adhesive portion and the lip portion, and the lip portion of the seal member that does not contact the blade surface is in contact with each other. An interblade spacer seal structure characterized by comprising:
JP17547895A 1995-06-19 1995-06-19 Interblade spacer seal structure Expired - Fee Related JP3684620B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP17547895A JP3684620B2 (en) 1995-06-19 1995-06-19 Interblade spacer seal structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP17547895A JP3684620B2 (en) 1995-06-19 1995-06-19 Interblade spacer seal structure

Publications (2)

Publication Number Publication Date
JPH094410A JPH094410A (en) 1997-01-07
JP3684620B2 true JP3684620B2 (en) 2005-08-17

Family

ID=15996753

Family Applications (1)

Application Number Title Priority Date Filing Date
JP17547895A Expired - Fee Related JP3684620B2 (en) 1995-06-19 1995-06-19 Interblade spacer seal structure

Country Status (1)

Country Link
JP (1) JP3684620B2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3078813A1 (en) * 2015-04-08 2016-10-12 United Technologies Corporation Fan section comprising a blade platform seal with leading edge winglet and associated gas turbine engine

Families Citing this family (6)

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Publication number Priority date Publication date Assignee Title
US6217283B1 (en) * 1999-04-20 2001-04-17 General Electric Company Composite fan platform
GB0611031D0 (en) 2006-06-06 2006-07-12 Rolls Royce Plc An aerofoil stage and a seal for use therein
GB0614640D0 (en) * 2006-07-22 2006-08-30 Rolls Royce Plc An annulus filler seal
FR2939836B1 (en) * 2008-12-12 2015-05-15 Snecma SEAL FOR PLATFORM SEAL IN A TURBOMACHINE ROTOR
FR2987086B1 (en) * 2012-02-22 2014-03-21 Snecma LINEAR JOINT OF PLATFORM INTER-AUBES
EP3438410B1 (en) 2017-08-01 2021-09-29 General Electric Company Sealing system for a rotary machine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3078813A1 (en) * 2015-04-08 2016-10-12 United Technologies Corporation Fan section comprising a blade platform seal with leading edge winglet and associated gas turbine engine
US9988920B2 (en) 2015-04-08 2018-06-05 United Technologies Corporation Fan blade platform seal with leading edge winglet

Also Published As

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