TW201323709A - Module of combustion turbine engine - Google Patents

Module of combustion turbine engine Download PDF

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TW201323709A
TW201323709A TW100144767A TW100144767A TW201323709A TW 201323709 A TW201323709 A TW 201323709A TW 100144767 A TW100144767 A TW 100144767A TW 100144767 A TW100144767 A TW 100144767A TW 201323709 A TW201323709 A TW 201323709A
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turbine
gas turbine
gas
module
compressor
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TW100144767A
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Chinese (zh)
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TWI482903B (en
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Sei-Ping Louh
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Hon Hai Prec Ind Co Ltd
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Abstract

This invention provides a module of combustion turbine engine which includes a gas turbine engine, and a turbine. The gas turbine engine comprises an air intake, a compressor, a combustion chamber, a turbine rotor and an air vent. The air intake on the front of the compressor, the compressor set in the rear of the combustion chamber, set between the combustion chamber and the air vent of the turbine rotor. The turbine set between the air vent and the air intake, the turbine has a first turbine rotor and a second turbine rotor with coaxial.

Description

燃氣渦輪機模組Gas turbine module

本發明涉及一種燃氣渦輪機模組,尤指一種可增加燃燒效率的燃氣渦輪機模組。The invention relates to a gas turbine module, in particular to a gas turbine module capable of increasing combustion efficiency.

一般油電混合動力車(Hybrid electric vehicle 簡稱HEV)使用內燃機及電動機作為動力來源,其中內燃機是將液體燃料或是氣體燃料與空氣混合後,直接輸入機器內部產生熱能再轉化為機械能的一種熱機,內燃機具有體積小、質量小、便於移動、熱效率高、起動性能好的特點。目前運用在車輛的燃氣渦輪機是屬於熱機的一種發動機,其主要包括有壓縮機、燃燒室、渦輪等部分,首先由壓縮機將通過進氣口進入的新鮮空氣加壓成為高壓氣體,接著通過噴油嘴噴出燃油與高壓氣體混合,進入燃燒室燃燒形成高溫高壓氣體,然後以該高溫高壓氣體推動渦輪,將熱能轉換為機械能輸出,最後廢氣則由排氣口排出於大氣之中。這些自燃氣渦輪機排出的廢氣通常仍然屬於高溫高壓的氣體,排除於大氣之中形成另一種能源的浪費,因此仍然有被回收再利用。例如;復熱式循環燃氣渦輪機以渦卷器(Scroll)、收集器(Collector)以及引氣道等,收集渦輪排出的高溫廢氣使進入燃燒室的高壓氣體溫度增高,可以提昇機組的熱效率並減少燃料的消耗量。但是,復熱式循環燃氣渦輪機只是利用高溫高壓廢氣中的熱能部分,對於仍然存在於廢氣中的壓力能尚未有效運用。A Hybrid electric vehicle (HEV) uses an internal combustion engine and an electric motor as a power source. The internal combustion engine is a heat engine that directly mixes liquid fuel or gaseous fuel with air and directly inputs heat into the machine to convert it into mechanical energy. The internal combustion engine has the characteristics of small volume, small mass, easy movement, high thermal efficiency and good starting performance. The gas turbine currently used in a vehicle is an engine of a heat engine, and mainly includes a compressor, a combustion chamber, a turbine and the like. First, the compressor pressurizes fresh air entering through the intake port into a high-pressure gas, and then passes through The fuel injected from the injector mixes with the high-pressure gas, enters the combustion chamber to form a high-temperature and high-pressure gas, and then drives the turbine with the high-temperature and high-pressure gas to convert the thermal energy into mechanical energy output, and finally the exhaust gas is discharged into the atmosphere through the exhaust port. These exhaust gases from gas turbines are still still high-temperature and high-pressure gases, which are excluded from the atmosphere and form another source of energy waste, so they are still recycled. For example, a regenerative cycle gas turbine collects high-temperature exhaust gas from a turbine with a scroll, a collector, and an air intake to increase the temperature of the high-pressure gas entering the combustion chamber, thereby improving the thermal efficiency of the unit and reducing Fuel consumption. However, the reheat cycle gas turbine only utilizes the portion of the heat energy in the high temperature and high pressure exhaust gas, and the pressure energy still present in the exhaust gas has not been effectively utilized.

有鑒於此,有必要提供可增加進氣壓力提升燃燒效率的一種燃氣渦輪機模組。In view of this, it is necessary to provide a gas turbine module that can increase the intake pressure and improve the combustion efficiency.

本發明提供一種燃氣渦輪機模組,其包括一燃氣渦輪以及一渦輪機。該燃氣渦輪包括一進氣口、一壓縮機、一燃燒室、一渦輪轉子以及一排氣口。該進氣口位於該壓縮機的前端,該壓縮機的後方設置該燃燒室,該燃燒室與該排氣口之間設置該渦輪轉子。該排氣口與該進氣口之間設置該渦輪機,該渦輪機具有同軸設置的一第一渦輪轉子及一第二渦輪轉子。The present invention provides a gas turbine module that includes a gas turbine and a turbine. The gas turbine includes an air inlet, a compressor, a combustion chamber, a turbine rotor, and an exhaust port. The air inlet is located at a front end of the compressor, and the combustion chamber is disposed behind the compressor, and the turbine rotor is disposed between the combustion chamber and the exhaust port. The turbine is disposed between the exhaust port and the intake port, and the turbine has a first turbine rotor and a second turbine rotor disposed coaxially.

相較現有技術,本發明的燃氣渦輪機模組,通過在該排氣口與該進氣口之間設置的該渦輪機,使該燃氣渦輪運作所排出的廢氣流可驅動該渦輪機在該排氣口設置具有的該第一渦輪轉子旋轉,該渦輪轉子同軸設置的該第二渦輪轉子將隨著一併旋轉,而該第二渦輪轉子位於該進氣口處,可對該壓縮機的進氣增壓,提高該燃燒室的進氣量與進氣壓力,從而可以有效提高該燃氣渦輪機的燃燒效率。Compared with the prior art, the gas turbine module of the present invention, through the turbine disposed between the exhaust port and the intake port, allows the exhaust gas flow discharged by the gas turbine to drive the turbine in the row The air port is provided with the rotation of the first turbine rotor, the second turbine rotor coaxially disposed on the turbine rotor will rotate together, and the second turbine rotor is located at the air inlet, and the compressor can be advanced The air pressure is increased to increase the intake air amount and the intake air pressure of the combustion chamber, so that the combustion efficiency of the gas turbine can be effectively improved.

下面將結合附圖對本發明作一個具體介紹。The present invention will be specifically described below with reference to the accompanying drawings.

請參閱圖1所示,為本發明燃氣渦輪機模組實施例的氣體流動示意圖,該渦輪機模組10,包括一燃氣渦輪12以及一渦輪機14。本實施例該燃氣渦輪12為復熱式循環燃氣渦輪機,該燃氣渦輪12除了包括一壓縮機122、一燃燒室124、一渦輪轉子126以外更具有一熱交換器128。該壓縮機122產生的高壓氣體首先會經過該熱交換器128,使該高壓氣體的溫度提高後再送進該燃燒室124,該燃燒室124以該增溫的高壓氣體混合燃料後,燃燒生成的高溫高壓氣體則驅動該渦輪轉子126,用以使熱能轉化為機械能對外界作功。例如,以該渦輪轉子126驅動一發電機20,使該發電機20對油電混合動力車的電力驅動馬達的電池(圖中未標示)提供電力,或是使該渦輪轉子126直接驅動油電混合動力車的傳動系統以提供燃料驅動的動力,當然該渦輪轉子126也可以同時軸向帶動該壓縮機122對空氣進行加壓。驅動該渦輪轉子126後的廢氣仍然具有高溫高壓,因此可以回收導引至該熱交換器128內,以該廢氣的高溫對該壓縮機122產生的高壓氣體進行熱交換,使該壓縮機122產生的高壓氣體溫度提高,從而提高該氣體進入該燃燒室124的燃燒效率。通過該熱交換器128的該廢氣雖然經過熱交換而降溫但是仍然具有壓力,因而可以導引至該渦輪機14處,藉由該廢氣的壓力提供驅動該渦輪機14的動力,使該渦輪機14對該壓縮機122的進氣進行增壓。該渦輪機14的增壓運作將使更多的氣體同時進入該壓縮機122,並使該壓縮機122進入該燃燒室124的壓力更大,從而更多的空氣以及更高的壓力在該燃燒室124燃爆,將可更加提昇該燃氣渦輪12對外輸出的動力。該燃氣渦輪12也可以是單段式燃氣渦輪機,該單段式燃氣渦輪機不具有該熱交換器128設置,該壓縮機122產生的高壓氣體直接進入該燃燒室124,該燃燒室124爆燃產生的高溫高壓氣體驅動該渦輪轉子126後的廢氣就導向該渦輪機14,用以驅動該渦輪機14對該壓縮機122的進氣進行增壓。Please refer to FIG. 1 , which is a schematic diagram of gas flow of an embodiment of a gas turbine module according to the present invention. The turbine module 10 includes a gas turbine 12 and a turbine 14 . In this embodiment, the gas turbine 12 is a reheating cycle gas turbine. The gas turbine 12 further includes a heat exchanger 128 in addition to a compressor 122, a combustion chamber 124, and a turbine rotor 126. The high-pressure gas generated by the compressor 122 first passes through the heat exchanger 128, and the temperature of the high-pressure gas is increased and then sent to the combustion chamber 124. The combustion chamber 124 is mixed with the warmed high-pressure gas and then burned. The high temperature and high pressure gas drives the turbine rotor 126 to convert thermal energy into mechanical energy to work on the outside. For example, the generator rotor 20 is driven by the turbine rotor 126 to provide power to the battery (not shown) of the electric drive motor of the hybrid electric vehicle, or to directly drive the turbine rotor 126. The drive train of the hybrid vehicle provides fuel-driven power. Of course, the turbine rotor 126 can also axially drive the compressor 122 to pressurize the air. The exhaust gas after driving the turbine rotor 126 still has a high temperature and a high pressure, so that it can be recovered and guided into the heat exchanger 128, and the high pressure gas generated by the compressor 122 is heat exchanged at a high temperature of the exhaust gas, so that the compressor 122 is generated. The high pressure gas temperature is increased to increase the combustion efficiency of the gas entering the combustion chamber 124. The exhaust gas passing through the heat exchanger 128, although cooled by heat exchange, still has pressure and can be directed to the turbine 14, by which the pressure of the exhaust gas provides power to drive the turbine 14, causing the turbine 14 to The intake air of the compressor 122 is pressurized. The boosting operation of the turbine 14 will cause more gas to enter the compressor 122 at the same time, and the compressor 122 will enter the combustion chamber 124 at a higher pressure, thereby providing more air and higher pressure in the combustion chamber. 124 blasting will further enhance the external output of the gas turbine 12. The gas turbine 12 can also be a single-stage gas turbine that does not have the heat exchanger 128 disposed, the high pressure gas produced by the compressor 122 directly entering the combustion chamber 124, the combustion chamber 124 The high temperature and high pressure gas generated by the deflagration drives the exhaust gas after the turbine rotor 126 is directed to the turbine 14 for driving the turbine 14 to pressurize the intake air of the compressor 122.

請再參閱圖2所示,為圖1燃氣渦輪機模組實施例的組合示意圖,該燃氣渦輪12設置在一機殼體120內,該機殼體120的同一側設置具有一進氣口121以及一排氣口123,該進氣口121位於該燃氣渦輪12的該壓縮機122前端,清淨的空氣可以由該進氣口121進入該壓縮機122進行空氣加壓的運作。該壓縮機122的後方設置該燃燒室124,使該壓縮機122加壓的空氣進入該燃燒室124與燃料混合並燃燒產生高溫高壓的氣體。該燃燒室124與該排氣口123之間設置該渦輪轉子126,使該渦輪轉子126被該燃燒室124產生的高溫高壓氣體驅動,該渦輪轉子126被驅動後的廢氣再由該排氣口123排出。該渦輪轉子126被驅動旋轉將帶動同軸連接的該壓縮機122以及一傳動軸125,該壓縮機122被帶動進行壓縮空氣的運作,該傳動軸125設置於該機殼體120外,被帶動進行對外界的作功。該排氣口123與該進氣口121之間設置該渦輪機14,該渦輪機14具有同軸設置的一第一渦輪轉子142及一第二渦輪轉子144。該第一渦輪轉子142位於該排氣口123處,該第二渦輪轉子144位於該進氣口121處。該第一渦輪轉子142受該排氣口123導出的該廢氣壓力作用產生旋轉的動力,該第一渦輪轉子142的旋轉動力驅動同軸設置的該第二渦輪轉子144旋轉運作。該第二渦輪轉子144的旋轉運作可在該進氣口121吸入更多的空氣,同時對進入該壓縮機122的空氣加壓。該第二渦輪轉子144在該進氣口121處的吸氣增壓,有助於該壓縮機122進入該燃燒室124的空氣量與壓力,使該燃燒室124可以燃燒更完全、燃燒效率更高。相較於一般單段式燃氣渦輪機在進氣口以自然進氣進行的壓縮燃燒,本發明該燃氣渦輪12具有以該廢氣驅動的該渦輪機14進行增壓燃燒,顯然可以獲得更高的燃燒效能與輸出功率。本實施例該燃氣渦輪12為復熱式循環燃氣渦輪機,就是除了上述利用該廢氣的壓力外,同時要運用該廢氣的熱量。該燃氣渦輪12的該排氣口123與該渦輪轉子126之間進一步設置該熱交換器128,並將該熱交換器128的位置設置位於該壓縮機122與該燃燒室124之間(如圖中虛線所標示的位置),使該熱交換器128可對進入該燃燒室124前的壓縮空氣進行熱交換,使進入該燃燒室124的空氣具有高溫、高壓及高飽和量,在燃燒時就能燃燒完全,提高燃燒效率產生更高的輸出功率。Referring to FIG. 2 again, it is a schematic diagram of a combination of the embodiment of the gas turbine module of FIG. 1. The gas turbine 12 is disposed in a casing 120. The same side of the casing 120 is provided with an air inlet. 121 and an exhaust port 123, the intake port 121 is located at the front end of the compressor 122 of the gas turbine 12, and the clean air can enter the compressor 122 through the air inlet 121 to perform air pressurization. The combustion chamber 124 is disposed behind the compressor 122, and the air pressurized by the compressor 122 enters the combustion chamber 124 to be mixed with fuel and combusted to generate a high temperature and high pressure gas. The turbine rotor 126 is disposed between the combustion chamber 124 and the exhaust port 123, and the turbine rotor 126 is driven by the high temperature and high pressure gas generated by the combustion chamber 124. The exhaust gas after the turbine rotor 126 is driven is further discharged from the exhaust port. 123 discharged. The turbine rotor 126 is driven to rotate to drive the coaxially connected compressor 122 and a drive shaft 125. The compressor 122 is driven to operate the compressed air. The drive shaft 125 is disposed outside the casing 120 and is driven. Work on the outside world. The turbine 14 is disposed between the exhaust port 123 and the intake port 121. The turbine 14 has a first turbine rotor 142 and a second turbine rotor 144 disposed coaxially. The first turbine rotor 142 is located at the exhaust port 123, and the second turbine rotor 144 is located at the air inlet 121. The first turbine rotor 142 is rotated by the exhaust gas pressure derived from the exhaust port 123, and the rotational power of the first turbine rotor 142 drives the coaxially disposed second turbine rotor 144 to rotate. The rotating operation of the second turbine rotor 144 can draw more air at the intake port 121 while pressurizing the air entering the compressor 122. The suction boost of the second turbine rotor 144 at the intake port 121 contributes to the amount of air and pressure of the compressor 122 entering the combustion chamber 124, so that the combustion chamber 124 can be burned more completely and the combustion efficiency is more efficient. high. Compared with the compression combustion of the conventional single-stage gas turbine with natural intake air at the intake port, the gas turbine 12 of the present invention has the turbomachine 14 driven by the exhaust gas for supercharged combustion, and it is apparent that a higher combustion can be obtained. Combustion efficiency and output power. In the present embodiment, the gas turbine 12 is a reheating type gas turbine, in which the heat of the exhaust gas is used in addition to the pressure of the exhaust gas. The heat exchanger 128 is further disposed between the exhaust port 123 of the gas turbine 12 and the turbine rotor 126, and the position of the heat exchanger 128 is disposed between the compressor 122 and the combustion chamber 124 (eg, The position indicated by the broken line in the figure enables the heat exchanger 128 to exchange heat with the compressed air before entering the combustion chamber 124, so that the air entering the combustion chamber 124 has high temperature, high pressure and high saturation amount during combustion. It can burn completely and improve combustion efficiency to produce higher output power.

本發明燃氣渦輪機模組,該燃氣渦輪12的該排氣口123與該進氣口121之間設置該渦輪機14,利用該排氣口123的該廢氣壓力驅動該渦輪機14,使該渦輪機14可在該進氣口121進行加壓進氣,從而該燃燒室124的進氣壓力可以被提昇,達到對該燃氣渦輪12的燃燒效率有效提高之功能。In the gas turbine module of the present invention, the turbine 14 is disposed between the exhaust port 123 of the gas turbine 12 and the intake port 121, and the turbine 14 is driven by the exhaust pressure of the exhaust port 123 to make the turbine The intake air can be pressurized at the intake port 121 so that the intake pressure of the combustion chamber 124 can be increased to achieve an effective improvement in the combustion efficiency of the gas turbine 12.

應該指出,上述實施例僅為本發明的較佳實施方式,本領域技術人員還可在本發明精神內做其他變化。這些依據本發明精神所做的變化,都應包含在本發明所要求保護的範圍之內。It should be noted that the above-described embodiments are merely preferred embodiments of the present invention, and those skilled in the art can make other changes within the spirit of the present invention. All changes made in accordance with the spirit of the invention are intended to be included within the scope of the invention.

10...渦輪機模組10. . . Turbine module

12...燃氣渦輪12. . . Gas turbine

121...進氣口121. . . Air inlet

122...壓縮機122. . . compressor

123...排氣口123. . . exhaust vent

124...燃燒室124. . . Combustion chamber

125...傳動軸125. . . transmission shaft

126...渦輪轉子126. . . Turbine rotor

128...熱交換器128. . . Heat exchanger

120...機殼體120. . . Machine housing

14...渦輪機14. . . Turbine

142...第一渦輪轉子142. . . First turbine rotor

144...第二渦輪轉子144. . . Second turbine rotor

20...發電機20. . . generator

圖1是本發明燃氣渦輪機模組實施例的氣體流動示意圖。BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 is a schematic illustration of gas flow for an embodiment of a gas turbine module of the present invention.

圖2是圖1的燃氣渦輪機模組實施例的組合示意圖。2 is a combined schematic view of the embodiment of the gas turbine module of FIG. 1.

10...渦輪機模組10. . . Turbine module

12...燃氣渦輪12. . . Gas turbine

121...進氣口121. . . Air inlet

122...壓縮機122. . . compressor

123...排氣口123. . . exhaust vent

124...燃燒室124. . . Combustion chamber

125...傳動軸125. . . transmission shaft

126...渦輪轉子126. . . Turbine rotor

128...熱交換器128. . . Heat exchanger

120...機殼體120. . . Machine housing

14...渦輪機14. . . Turbine

142...第一渦輪轉子142. . . First turbine rotor

144...第二渦輪轉子144. . . Second turbine rotor

Claims (10)

一種燃氣渦輪機模組,其包括一燃氣渦輪以及一渦輪機,該燃氣渦輪包括一進氣口、一壓縮機、一燃燒室、一渦輪轉子以及一排氣口,該進氣口位於該壓縮機的前端,該壓縮機的後方設置該燃燒室,該燃燒室與該排氣口之間設置該渦輪轉子,該排氣口與該進氣口之間設置該渦輪機,該渦輪機具有同軸設置的一第一渦輪轉子及一第二渦輪轉子。A gas turbine module includes a gas turbine and a turbine, the gas turbine including an air inlet, a compressor, a combustion chamber, a turbine rotor, and an exhaust port, the air inlet is located at the a front end of the compressor, the combustion chamber is disposed behind the compressor, the turbine rotor is disposed between the combustion chamber and the exhaust port, and the turbine is disposed between the exhaust port and the air inlet, the turbine has a coaxial arrangement a first turbine rotor and a second turbine rotor. 如申請專利範圍第1項所述的燃氣渦輪機模組,其中,該燃氣渦輪設置在一機殼體內,該機殼體的同一側設置該進氣口以及該排氣口。The gas turbine module of claim 1, wherein the gas turbine is disposed in a casing, and the air inlet and the exhaust port are disposed on the same side of the casing. 如申請專利範圍第2項所述的燃氣渦輪機模組,其中,該渦輪轉子同軸連接該壓縮機以及一傳動軸,該傳動軸設置於該機殼體外。The gas turbine module of claim 2, wherein the turbine rotor is coaxially coupled to the compressor and a drive shaft, the drive shaft being disposed outside the housing. 如申請專利範圍第3項所述的燃氣渦輪機模組,其中,該渦輪轉子驅動一發電機,該發電機對油電混合動力車的電力驅動馬達的電池提供電力。The gas turbine module of claim 3, wherein the turbine rotor drives a generator that supplies power to a battery of an electric drive motor of the hybrid electric vehicle. 如申請專利範圍第4項所述的燃氣渦輪機模組,其中,該渦輪轉子驅動油電混合動力車的傳動系統以提供燃料驅動的動力。The gas turbine module of claim 4, wherein the turbine rotor drives a transmission system of the hybrid electric vehicle to provide fuel-driven power. 如申請專利範圍第1項所述的燃氣渦輪機模組,其中,該第一渦輪轉子位於該排氣口處,該排氣口導出的廢氣壓力作用於該第一渦輪轉子。The gas turbine module of claim 1, wherein the first turbine rotor is located at the exhaust port, and exhaust gas pressure derived from the exhaust port acts on the first turbine rotor. 如申請專利範圍第1項所述的燃氣渦輪機模組,其中,該第二渦輪轉子位於該進氣口處。The gas turbine module of claim 1, wherein the second turbine rotor is located at the intake port. 如申請專利範圍第1項所述的燃氣渦輪機模組,其中,該燃氣渦輪為單段式燃氣渦輪機。The gas turbine module of claim 1, wherein the gas turbine is a single-stage gas turbine. 如申請專利範圍第1項所述的燃氣渦輪機模組,其中,該燃氣渦輪為復熱式循環燃氣渦輪機,該排氣口與該渦輪轉子之間進一步設置一熱交換器。The gas turbine module of claim 1, wherein the gas turbine is a reheating cycle gas turbine, and a heat exchanger is further disposed between the exhaust port and the turbine rotor. 如申請專利範圍第9項所述的燃氣渦輪機模組,其中,該熱交換器位於該壓縮機與該燃燒室之間。The gas turbine module of claim 9, wherein the heat exchanger is located between the compressor and the combustion chamber.
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