M416739 . 五、新型說明： 【新型所屬之技術領域】 本創作係關於一種内燃機氣渦輪裝置，特別是一種適 用於内燃機氣流流動系統之管路内，用以提升氣流強度及 ‘ 風速以改善内燃機動力的内燃機氣渦輪裝置。 【先前技術】 一般内燃機均會設置一氣渦輪或類似裝置，以對内燃 • 機之燃燒室提供大量的高密度空氣，藉由增加供應至燃燒 室之氣流流動循環力量，以及增加單位時間内之氣流流動 速率，使内燃機之燃燒作用完全以增加内燃機動力。惟， 習知的氣渦輪或類似裝置，易因氣流流動旋轉而產生氣流 阻力，使增進内燃機動力之效果受到限制。 為解決上述問題，中華民國公告第593937號「内燃 機氣渴輪翼片結構」專利案，揭示了 一種内燃機氣渦輪翼 片結構9,請參照第丨圖’其係包含一定位件“及一葉片 鲁 組92 ’該葉片組92具有複數個葉片92卜該定位件91内 σ卩係呈中空狀，且該定位件91設有複數個結合孔911 ;該 • 葉片組92係用以加速和增進氣流迴轉循環，該複數個葉片 921係以傾斜和徑向輻射狀裝設於該定位件91内部，每一 葉片921均設有一結合部922，以分別與該定位件91之複 數個結合孔911卡固結合。此外，該葉片921設有貫穿二 表面之至少一氣流孔923，以避免該葉片921在負壓力區 產生旋渦而形成氣流阻力，且該葉片921於氣流孔923處 凸°又有一辅助葉片924，使氣流碰撞葉片921表面後皆會 —3 — 形成直線前進。 然而，由於該内燃機氣渦輪翼片結構9之葉片組92 倾=由複數個葉片921所組成，且該複數個葉片921係呈 嫩斜T徑向輻射狀地裝設於定位件91内部，因此進入該内 =广氧渦輪翼片結構9之氣流，將立即地受到許多風阻而 速。此外，流經葉片組92之氣流，雖可隨傾斜設置 =數個葉片921而略微改變氣流角度，以於出口端產生 旋轉4進的氣流，但因受風阻影響加上改變氣流的角度 有限，使得流出的氣流即使可旋轉前進而具有加壓效果， 但氣流旋動的力道卻會很快地消失，令加壓效果受限，因 此通$品於内燃機氣流流動系統中（例如：空氣濾、清器前 後、節氣門前後、内燃機各進氣門處、排氣管中等位置） 裝設多個内燃機氣渦輪翼片結構9，方可使加壓而提高空 氣密度之效果持續送達内燃機的燃燒室，故裝設成本較 高，從而直接影響該内燃機氣渦輪翼片結構9之商業價值。 【新型内容】 本創作之主要目的係提供一種内燃機氣渦輪裝置，係 可產生螺旋形氣流，以提升氣流強度及風速者。 本創作之次一目的係提供一種内燃機氣渦輪裝置，係 可減少風阻’以提升氣流流動之順暢度而維持加壓效果者。 為達到前述目的’本創作所運用之技術内容包含有. 一種内燃機氣渦輪裝置，係包含··二定位件，同轴且 互呈平行地間隔設置；及一導流件，兩端分別形成一第一 邊及一第二邊，該第一邊與其中一定位件結合以形成一進 -第—邊與另—定位件結合以形成—排氣部，兮第 邊與第二邊形成一夾角。 B亥弟 本創作之内燃機氣渦輪農 :別r該第-邊及第二邊二 第二邊及第四邊呈斜向設置於該二定位件之間。这 本創作之内燃機氣渴輪|置，其中，該導 =，該導流件之第-邊及第二邊相對扭轉而形;L 於該中心點之一第一彎折線及-第二彎折線。 錯 對燃機氣渦輪裝置，其中，該導流件具有相 對應之_表面，該導流件的兩端之間，在該導流件之 =’=導流件相鄰之二邊界與該第—f折線 _ Γ導流部，以及在該導流件之另—表面，以該導流件= 狀二邊界與該第二彎折_成相對應之二導流部。 本創作之内燃機氣渦輪裳置，其中， 邊之夾角為90度。 您/、弟一 本創作之内燃機氣渴輪裝置，其中，該第三邊及第四 邊為弧形雜，並齡贿_氣膽裝 管體的内周壁。 機:渦輪裝置，其中，該導流件兩端的 長度刀別等於或略小於該二定位件之内徑。 本創作之内燃機氣渦輪裝置，其中，該 軸向設有一開口槽。 又m忏今/〇 【實施方式】 為讓本創作之上述及其他目的、特徵及優點能更明顯 M416739 易懂，下文特舉本創作之較佳實施例，並配合所附圖式， 作詳細說明如下： 凊參閱第2圖’其係為本創作内燃機氣渦輪裝置—車* 佳實施例之立體分解圖。在本實施例中，該内燃機氣渦^ 装置包含二定位件1及一導流件2，該導流件2係結合於 該二定位件1之間；該二定位件1及該導流件2可以是由 不銹鋼、炭鋼、銅等具有耐高溫及酸驗之特性的材料所製 二定位件1各可以為一圓環體，並呈同軸且相互平行 地間隔設置，於裝設時，該二定位件丨之外周壁可用以: 合貼接於内燃機氣流流動系統之一管體的内周壁。該二定 位件1共同具有一軸線A，該二定位件丨還可以各沿平行 2軸ί A之方向開設一開口槽11，使該二定位件1可微調 徑向寬度，以適應所裝設之管體在製造時所產生的内徑公 ，。另’為使說明更加清楚，以下將二粒件！分別標示 為la及lb。 …^ ^乂田一板體彎折形成，或由數個板體以 3其他結合方式連接而成。該導流件2具有相對應之 表面及第一表面，且該導流件2在轴線a方向上 兩端分別形成-第-邊21及-第二邊22，該導流件2 ，分別連接該第-邊21及第二邊22之—^邊1 ’四邊24。其中，該第一邊21與第二邊22形成一夾角 (如第3c圖所示）。 睛參閱第2及3a至3c圖，導流件2具有—中心點^ 在本實施例中，該導流件2係由一板體彎折形成因此] —6 — M416739 導流件2能夠以該中心點P為中心，將該第一邊21與第二 邊22相對扭轉而成型，使該導流件2形成交錯於該中心點 P之一第一彎折線25及一第二彎折線26。其中，在導流件 2之第一表面上，該第一邊21、第四邊24及第一彎折線 25共同構成一第一導流部2a，該第二邊22、第三邊23及 第一彎折線25共同構成一第二導流部2b ;同理，在導流 件2之第二表面上，則由該第一邊21、第三邊23及第二 彎折線26共同構成一第一導流部2a，該第二邊22、第四 邊24及第二彎折線26共同構成一第二導流部2b。 該導流件2之第一邊21與第二邊22的長度，約等於 或略小於二定位件la、lb之内徑，使導流件2能夠以第一 邊21與定位件la結合而形成一進氣部3，以及以第二邊 22與定位件lb結合而形成一排氣部4。據此，該導流件2 之第一邊21可將該進氣部3區隔成二進氣口，使氣流分別 從該進氣部3之二進氣口導入，並使該二氣流分別循該導 流件2之第一表面及第二表面之第一導流部2a及第二導流 部2b導引，以改變氣流的流動角度。 在本實施例中，該導流件2之第一邊21與第二邊22 之夾角0 (即相對的扭轉/設置角度）可以為90度，且第 三邊23及第四邊24可以呈斜向設置於該二定位件la、lb 之間，並於空間中呈現近似X形之交錯態樣，據以在最短 的設置距離下，有效改變氣流的流動角度，使氣流可以呈 螺旋形態樣旋轉傳送。 其中，本創作之内燃機氣渦輪裝置係無特定的裝設方 向，因此也可以將導流件2之第二邊22與定位件lb結合 —7 — 3部^為進氣部3，導流件2之第，邊21與定位件la :卩作為排氣部4 ’使得導流件2之第二邊22可將 該進氣部3區隔成二進氣口以分導入氣流， 分別循該導流件2之第—表面及第二表*之第—導；；二 及第一導流部2b導引而導向排氣部4。又，為具有穩固結 合的定位效果，在本實施例中，導流件2與二定位件“、 lb之結合方式，可以選擇將導流件2之第—邊。及第二 邊22兩側與部分的第三邊23及第四邊24，以焊接等方式 分別固接於二定位件la、lb之内緣。 另，為使本創作之内燃機氣渦輪裝置裝設於内燃機氣 流流動系統之一管體内時，能夠將流入進氣部3之氣流， 確實地以兩股氣流分別從導流件2之第一表面及第二表面 導向排氣部4 ’該第三邊23及第四邊24較佳為弧形態樣， 使該第三邊23及第四邊24幾乎可以貼合於管體之内周 壁，以減少部分氣流由第一導流部2a滲漏至第二導流部 2b的情況。 請參照第4圖，從進氣部3直線送入之氣流，可以被 導流件2之一端邊（在本實施例中為第一邊21)切割成二 股氣流，並分別流入進氣部3之二進氣口，以分別循導流 件2之第一表面及第—表面前進。流通於導流件2之第一 表面的氣流（圖中以實線表示），係透過第—導流部&之 導引而改變流動角度’續於流人第二導流部⑪時再次改變 流動角度，以從排氣部4流出螺旋形的氣流；相對地，流 通於導流件2之第二表面的氣流（圖中以虛線表示）亦受 第二表面之第-導流部2a及第二導流部2b導引而以螺旋 形的氣流形式從排氣部4流出。藉由螺旋形氣流具有可在 小耗圍内產生大迴旋力之特性，增強氣流的強度。 其中’因流經内燃機氣渦輪裝置之氣流，僅會被導流 件2分為兩股氣流，相較於習知的内燃機氣渦輪翼片結構 9’本創作之内燃機氣渦輪裝置具有較小的風阻，故可增加 早位時_之氣流流動縣。料，兩關向之螺旋形氣 流，更可在流出排氣部4後結合，以增強氣流結構並進一 步提高流速，從而達到提升氣流流動效率之功效。 請參照第5圖，為提升内燃機5性能，使用者可視需 求將複數__氣渦輪裝置裝設於内燃機氣流流動系統 中，在本實關中’可以僅選擇使用二個_機氣渦輪裝 置’並分職設於節氣Η 51後方之進氣岐f 52内，以及 内燃機5與消音器㈣之排氣管54 ί^並於使用時透過 溫度升高之熱漲效果，使各内燃機氣渦輪裝置之二定位件 1，可牢隨合在所配置之管财。此外，本㈣之内燃 機氣渦輪裝置使用時，較佳可於排氣管54中配合裝設一伸 ，翼片迴壓裝置6 ’以隨使用情形對内燃機5產生適當迴 麗；該伸縮翼>1迴壓裝置6之詳細結構說明可以參照申請 第99225787鮮利s，且該伸縮S #迴壓裝置6係裝設於 内燃機氣渦輪裝置與内燃機5之間。 故，從空氣濾清器55流出之氣流，可藉由節氣門51 調整流量而進入進氣岐管52;流入進氣岐管52内的氣流， 則透過内燃機氣渦輪裝置，在低風阻的情況下形成強勁且 高流速之螺旋形氣流並流入内燃機5，據以快速地對内燃 機5之燃燒至提供大量的高密度空氣，使内燃機$之燃燒 M416739 作用完全而增加内燃機5動力。同時，伸縮翼片迴壓裝置 6還可以隨使用情形對内燃機5產生適當迴壓，以促使油 氣燃燒元全而幫助内燃機5發揮扭力爆發，並配合裝設於 伸縮翼片迴壓裝置6與消音器53之間的内燃機氣渦輪裝 置’使氣流通過伸縮翼片迴壓裝置6後，能夠快速地被排 出’以避免排氣管54内積風而發生缸爆意外。 本創作之内燃機氣渦輪裝置，係可改變氣流的流動角 度’而以螺旋形氣流之形式流出，從而產生較大的迴旋力 以提升氣流的強度及風速，具有可改善内燃機5動力之功 效0 本創作之内燃機氣渦輪裝置，係可減少風阻，提升氣 流流動的順暢度，並使流出的氣流具有較佳的旋轉速率， 以維持加壓效果’令内燃機氣流流動系統中所需裝設之内 燃機氣渦輪裝置的數量得以減少，具有降低裝設成本之功 效。 雖然本創作已利用上述較佳實施例揭示，然其並非用 以限定本創作，任何熟習此技藝者在不脫離本創作之精神 和範圍之内，相對上述實施例進行各種更動與修改仍屬本 創作所保護之技術齡，@此本_之賴_當視後附 之申請專利範圍所界定者為準。 【圖式簡單說明】 第1圖：習知内燃機氣渦輪翼片結構之立體分解圖。 第2圖·本創作較佳實施例之立體分解圖。 M416739 第3a圖：本創作較佳實施例之侧視圖。 第3b圖：本創作較佳實施例之俯視圖。 第3c圖：本創作較佳實施例之後視圖。 第4圖：本創作較佳實施例之氣流示意圖。 第5圖：本創作較佳實施例裝設於内燃機氣流流動系統 中之配置圖。 【主要元件符號說明】 〔本創作〕 1 定位件 la 定位件 lb 定位件 11 開口槽 2 導流件 2a 第一導流部 2b 第二導流部 21 第一邊 22 第二邊 23 第三邊 24 第四邊 25 第一彎折線 26 第二彎折線 3 進氣部 4 排氣部 5 内燃機 51 節氣門 52 進氣岐管 53 消音器 54 排氣管 55 空氣濾清器 6 伸縮翼片迴壓裝置 A 軸線 θ 夾角 11 M416739 P 中心點 〔習知〕 9 氣渦輪翼片結構 91 911結合孔 92 921葉片 922 923氣流孔 924 定位件 葉片組 結合部 輔助葉片 —12 —M416739 . V. New description: [New technical field] This paper is about an internal combustion engine gas turbine device, especially a pipeline suitable for the internal combustion engine airflow system to improve the airflow intensity and 'wind speed to improve the internal combustion engine power. Internal combustion engine gas turbine unit. [Prior Art] A general-purpose internal combustion engine is provided with a gas turbine or the like to supply a large amount of high-density air to the combustion chamber of the internal combustion engine, by increasing the flow circulation force of the airflow supplied to the combustion chamber, and increasing the airflow per unit time. The flow rate makes the combustion of the internal combustion engine completely increase the power of the internal combustion engine. However, conventional gas turbines or the like are liable to generate airflow resistance due to the rotation of the airflow, which limits the effect of enhancing the power of the internal combustion engine. In order to solve the above problems, the Republic of China Announcement No. 593937 "Internal combustion engine thirsty wheel fin structure" patent case discloses an internal combustion engine gas turbine wing structure 9, please refer to the figure "the system includes a positioning member" and a blade The group 92 has a plurality of blades 92. The σ system is hollow in the positioning member 91, and the positioning member 91 is provided with a plurality of coupling holes 911. The blade group 92 is used for acceleration and promotion. In the air circulation cycle, the plurality of blades 921 are installed in the interior of the positioning member 91 in an inclined and radial direction. Each of the blades 921 is provided with a joint portion 922 for respectively engaging with a plurality of coupling holes 911 of the positioning member 91. In addition, the blade 921 is provided with at least one airflow hole 923 extending through the two surfaces to prevent the blade 921 from generating a vortex in the negative pressure region to form airflow resistance, and the blade 921 has a convexity at the airflow hole 923. The auxiliary blade 924 causes the airflow to collide with the surface of the blade 921 to form a straight forward. However, since the blade group 92 of the internal combustion engine gas turbine fin structure 9 is composed of a plurality of blades 921, and the complex A plurality of blades 921 are radially disposed radially inside the positioning member 91, so that the airflow entering the inner = wide oxygen turbine vane structure 9 will immediately be subjected to a lot of wind resistance and speed. The airflow of the blade group 92 can slightly change the airflow angle with the inclination setting=several blades 921 to generate a swirling airflow at the outlet end, but the airflow is limited due to the influence of the wind resistance and the airflow is limited. Even if it can be rotated forward and has a pressurizing effect, the force of the airflow swirling will disappear quickly, and the pressurization effect is limited, so that it is used in the airflow system of the internal combustion engine (for example, before and after the air filter, the cleaner, Before and after the throttle valve, at the intake valves of the internal combustion engine and at the exhaust pipe, a plurality of internal combustion engine gas turbine fin structures 9 are installed, so that the effect of increasing the air density by pressurization can be continuously delivered to the combustion chamber of the internal combustion engine, so that the installation is performed. The cost is high, which directly affects the commercial value of the gas turbine airfoil structure 9 of the internal combustion engine. [New content] The main purpose of the present invention is to provide a gas turbine device for an internal combustion engine, which can generate The spiral airflow is used to increase the airflow intensity and wind speed. The second objective of this creation is to provide a gas turbine device for internal combustion engine, which can reduce the wind resistance 'to improve the smoothness of the airflow and maintain the pressure effect. To achieve the above purpose' The technical content of the present invention includes: an internal combustion engine gas turbine device comprising two positioning members coaxially and spaced apart from each other; and a flow guiding member having a first side and a first end respectively formed The second side, the first side is combined with one of the positioning members to form an in-side-side and the other-positioning member to form an exhaust portion, and the first side forms an angle with the second side. The created internal combustion engine gas turbine farmer: the second side and the fourth side of the first side and the second side are disposed obliquely between the two positioning members. The creation of the internal combustion engine thirst wheel|position, wherein the guide =, the first side and the second side of the flow guide are relatively twisted; L is the first bending line of the center point and - the second bend Polyline. a misaligned gas turbine apparatus, wherein the flow guiding member has a corresponding surface, between the two ends of the flow guiding member, at the boundary of the flow guiding member = '= the flow guiding member adjacent to the boundary a first f-line _ Γ diversion portion, and a second flow guiding portion corresponding to the second bending yoke at the other surface of the flow guiding member. The internal combustion engine of the present invention is placed in a gas turbine, wherein the angle between the sides is 90 degrees. You/, brother, created the internal combustion engine thirst wheel device, in which the third side and the fourth side are curved and mixed, and the inner peripheral wall of the body of the bribe. Machine: A turbine device, wherein the length of the two ends of the flow guide is equal to or slightly smaller than the inner diameter of the two positioning members. The internal combustion engine gas turbine device of the present invention, wherein the axial direction is provided with an open groove. M 忏 〇 〇 实施 实施 实施 实施 实施 实施 实施 实施 实施 实施 实施 M M 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 416 The explanation is as follows: 凊 Refer to Fig. 2, which is a perspective exploded view of the preferred embodiment of the air-turbine engine of the internal combustion engine. In this embodiment, the internal combustion engine gas vortex device comprises two positioning members 1 and a flow guiding member 2, and the flow guiding member 2 is coupled between the two positioning members 1; the two positioning members 1 and the flow guiding member 2 may be made of materials such as stainless steel, carbon steel, copper and the like having high temperature resistance and acid resistance. The two positioning members 1 may each be a circular ring body and arranged coaxially and parallel to each other. The outer peripheral wall of the two positioning members can be used to: fit the inner peripheral wall of one of the tubes of the internal combustion engine airflow system. The two positioning members 1 have an axis A, and the two positioning members can also open an opening slot 11 in the direction of the parallel two axes, so that the two positioning members 1 can finely adjust the radial width to suit the installation. The inner diameter of the pipe body produced at the time of manufacture is public. Another 'To make the description clearer, the following will be two pieces! Marked as la and lb, respectively. ...^ ^The slab of the 乂田 is formed by bending, or it is made up of several plates combined by 3 other combinations. The flow guiding member 2 has a corresponding surface and a first surface, and the flow guiding member 2 respectively forms a first side - a second side 22 and a second side 22 in the direction of the axis a, respectively, the flow guiding member 2, respectively The first side 21 and the second side 22 are connected to each other. Wherein, the first side 21 forms an angle with the second side 22 (as shown in Fig. 3c). Referring to Figures 2 and 3a to 3c, the flow guiding member 2 has a center point. In the present embodiment, the flow guiding member 2 is formed by bending a plate body. Therefore, the M416739 guiding member 2 can be The center point P is centered, and the first side 21 and the second side 22 are oppositely twisted to form, so that the flow guiding member 2 forms a first bending line 25 and a second bending line 26 which are staggered at the center point P. . The first side 21, the fourth side 24, and the first bending line 25 together form a first guiding portion 2a, the second side 22 and the third side 23 of the first surface 21 and the first bending line 25 The first bending line 25 together constitutes a second flow guiding portion 2b. Similarly, on the second surface of the flow guiding member 2, the first side 21, the third side 23 and the second bending line 26 form a common The first flow guiding portion 2a, the second side 22, the fourth side 24 and the second bending line 26 together constitute a second flow guiding portion 2b. The length of the first side 21 and the second side 22 of the flow guiding member 2 is approximately equal to or slightly smaller than the inner diameters of the two positioning members la, lb, so that the flow guiding member 2 can be coupled with the positioning member la with the first side 21 An air inlet portion 3 is formed, and the second side 22 is combined with the positioning member 1b to form an exhaust portion 4. Accordingly, the first side 21 of the flow guiding member 2 can partition the air inlet portion 3 into two air inlets, and the air flow is respectively introduced from the two air inlets of the air inlet portion 3, and the two air currents are respectively separated. The first flow guiding portion 2a and the second flow guiding portion 2b of the first surface and the second surface of the flow guiding member 2 are guided to change the flow angle of the airflow. In this embodiment, the angle 0 between the first side 21 and the second side 22 of the flow guiding member 2 (ie, the relative twist/set angle) may be 90 degrees, and the third side 23 and the fourth side 24 may be The oblique direction is disposed between the two positioning members la, lb, and presents an approximately X-shaped staggered pattern in the space, so as to effectively change the flow angle of the airflow at the shortest set distance, so that the airflow can be in a spiral shape. Rotate the transfer. Wherein, the internal combustion engine gas turbine device of the present invention has no specific installation direction, so the second side 22 of the flow guiding member 2 can also be combined with the positioning member 1b - 7 - 3 parts are the intake portion 3, the flow guiding member 2, the side 21 and the positioning member la: 卩 as the exhaust portion 4' such that the second side 22 of the flow guiding member 2 can divide the air inlet portion 3 into two air inlets to introduce airflow, respectively The first surface of the flow guide 2 and the first surface of the second table *; and the first and second flow guiding portions 2b are guided to the exhaust portion 4. Moreover, in order to have a positioning effect with a stable combination, in the embodiment, the combination of the flow guiding member 2 and the two positioning members ", lb" may select the first side of the flow guiding member 2 and the two sides of the second side 22 And the third side 23 and the fourth side 24 of the part are respectively fixed to the inner edges of the two positioning members 1a and 1b by welding or the like. In addition, the engine air turbine device of the present invention is installed in the airflow system of the internal combustion engine. When the inside of the tube is inside, the airflow flowing into the air inlet portion 3 can be reliably guided by the two air currents from the first surface and the second surface of the flow guiding member 2 to the exhaust portion 4'. The third side 23 and the fourth portion The edge 24 is preferably in the form of an arc, so that the third side 23 and the fourth side 24 can be closely attached to the inner peripheral wall of the pipe body to reduce leakage of part of the air flow from the first flow guiding portion 2a to the second flow guiding portion. In the case of 2b, referring to Fig. 4, the airflow fed straight from the air inlet portion 3 can be cut into two airflows by one end side (in the present embodiment, the first side 21), and flows in separately. The two inlets of the inlet portion 3 are respectively advanced through the first surface and the first surface of the flow guiding member 2. The air flow on the first surface of the member 2 (shown by the solid line in the figure) is changed by the guidance of the first flow guiding portion & and the flow angle is changed again when the second flow guiding portion 11 is flown, The spiral airflow flows out from the exhaust portion 4; relatively, the airflow (shown by a broken line in the figure) flowing through the second surface of the flow guide 2 is also subjected to the first-flowing portion 2a and the second guide of the second surface The flow portion 2b is guided to flow out of the exhaust portion 4 in the form of a spiral air flow. The spiral air flow has the characteristic of generating a large swirling force within a small consumption range, thereby enhancing the strength of the air flow. The airflow of the turbine device is only divided into two airflows by the flow guiding member 2, compared with the conventional internal combustion engine gas turbine airfoil structure 9'. The internal combustion engine gas turbine device has a small wind resistance, so the early position can be increased. At the same time, the airflow flows to the county. The material, the two spiral spiral airflows, can be combined after flowing out of the exhaust portion 4 to enhance the airflow structure and further increase the flow rate, thereby improving the efficiency of the airflow flow. Figure, in order to improve the performance of the internal combustion engine 5, The user can install the plural __ gas turbine device in the airflow system of the internal combustion engine according to the needs of the user. In this actual case, 'only two _ gas turbine devices can be selected' and the air intake 设 located behind the throttle Η 51 can be divided. In f 52, and the exhaust pipe 54 of the internal combustion engine 5 and the muffler (4), and the heat rising effect of the temperature increase during use, the two positioning members 1 of the gas turbine devices of the internal combustion engine can be configured in accordance with the configuration. In addition, when the air turbine device of the internal combustion engine of the present invention is used, it is preferable to fit the extension in the exhaust pipe 54, and the airbag back pressure device 6' can appropriately return the internal combustion engine 5 according to the use situation; For a detailed description of the configuration of the telescopic wing > 1 back pressure device 6, reference is made to application No. 99925787, and the telescopic S# back pressure device 6 is installed between the internal combustion engine gas turbine device and the internal combustion engine 5. Therefore, the airflow flowing out of the air cleaner 55 can be adjusted to flow into the intake manifold 52 by the throttle valve 51; the airflow flowing into the intake manifold 52 passes through the gas turbine of the internal combustion engine, in the case of low wind resistance. A strong and high flow rate spiral flow is formed and flows into the internal combustion engine 5, whereby the combustion of the internal combustion engine 5 is rapidly supplied to provide a large amount of high-density air, so that the combustion of the internal combustion engine $M416739 is fully utilized to increase the power of the internal combustion engine 5. At the same time, the telescopic flap back pressure device 6 can also generate an appropriate back pressure for the internal combustion engine 5 according to the use situation, so as to promote the combustion of the oil and gas to help the internal combustion engine 5 to exert a torque burst, and cooperate with the telescopic flap back pressure device 6 and silencer. The internal combustion engine gas turbine device ' between the compressors 53 allows the airflow to pass through the bellows back pressure device 6 and can be quickly discharged' to avoid accumulation of wind in the exhaust pipe 54 to cause a cylinder explosion accident. The gas turbine device of the present invention can change the flow angle of the airflow and flow out in the form of a spiral airflow, thereby generating a large swirling force to enhance the strength and wind speed of the airflow, and has the function of improving the power of the internal combustion engine 5 The internal combustion engine gas turbine device is designed to reduce the wind resistance, improve the smooth flow of the airflow, and provide a better rotation rate of the outflowing airflow to maintain the pressure effect, which is required to make the internal combustion engine gas installed in the internal combustion engine airflow system. The number of turbine devices is reduced, which has the effect of reducing installation costs. Although the present invention has been disclosed by the above-described preferred embodiments, it is not intended to limit the present invention, and it is still within the spirit and scope of the present invention to make various changes and modifications to the above embodiments. The technical age protected by the creation, @本本_之赖_ is subject to the definition of the patent application scope attached. BRIEF DESCRIPTION OF THE DRAWINGS Fig. 1 is a perspective exploded view of a conventional gas turbine blade structure of an internal combustion engine. Fig. 2 is a perspective exploded view of the preferred embodiment of the present invention. M416739 Figure 3a: Side view of a preferred embodiment of the present invention. Figure 3b is a top plan view of a preferred embodiment of the present invention. Figure 3c: Rear view of the preferred embodiment of the present invention. Figure 4 is a schematic view of the gas flow of the preferred embodiment of the present invention. Fig. 5 is a layout view showing a preferred embodiment of the present invention installed in an air flow system of an internal combustion engine. [Main component symbol description] [This creation] 1 Positioning member la Positioning member lb Positioning member 11 Opening groove 2 Flow guiding member 2a First flow guiding portion 2b Second flow guiding portion 21 First side 22 Second side 23 Third side 24 Fourth side 25 First bending line 26 Second bending line 3 Intake part 4 Exhaust part 5 Internal combustion engine 51 Throttle 52 Intake manifold 53 Silencer 54 Exhaust pipe 55 Air filter 6 Telescopic flap back pressure Device A axis θ angle 11 M416739 P center point [known] 9 gas turbine wing structure 91 911 joint hole 92 921 blade 922 923 air flow hole 924 positioning piece blade group joint auxiliary blade - 12 -