JPH01190274A - Space solar power generation system - Google Patents
Space solar power generation systemInfo
- Publication number
- JPH01190274A JPH01190274A JP63010723A JP1072388A JPH01190274A JP H01190274 A JPH01190274 A JP H01190274A JP 63010723 A JP63010723 A JP 63010723A JP 1072388 A JP1072388 A JP 1072388A JP H01190274 A JPH01190274 A JP H01190274A
- Authority
- JP
- Japan
- Prior art keywords
- heat
- power generation
- thermoelectric element
- circulating
- passage
- 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
- 238000010248 power generation Methods 0.000 title claims abstract description 29
- 238000005338 heat storage Methods 0.000 claims description 12
- 230000005611 electricity Effects 0.000 abstract description 11
- 238000010438 heat treatment Methods 0.000 abstract 5
- 239000002775 capsule Substances 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 5
- YXFVVABEGXRONW-UHFFFAOYSA-N Toluene Chemical compound CC1=CC=CC=C1 YXFVVABEGXRONW-UHFFFAOYSA-N 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000008023 solidification Effects 0.000 description 2
- 238000007711 solidification Methods 0.000 description 2
- 230000032683 aging Effects 0.000 description 1
- 239000000969 carrier Substances 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
- F24S20/00—Solar heat collectors specially adapted for particular uses or environments
- F24S20/20—Solar heat collectors for receiving concentrated solar energy, e.g. receivers for solar power plants
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/40—Solar thermal energy, e.g. solar towers
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Thermal Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は太陽熱発電システムに係り、特に宇宙空間で用
いるのに好適な宇宙太陽熱発電システムに関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a solar thermal power generation system, and particularly to a space solar thermal power generation system suitable for use in outer space.
従来、宇宙太陽熱発電システムについては、ニス・ニー
・イー、Ｎｏ８５９２２０（１９８５年）第１．２２８
項から第１．２４５項（ＳＡＥ、Ｎｏ８５９２２０（１
９８５）Ｐｐｌ、２２８−１．２４５）において論じら
れている。同文献においては、宇宙太陽熱発電システム
の熱機関として、ランキンエンジンが有力とされている
。ランキンエンジン睨動用の循環熱媒体としては、極低
温の宇宙空間で使用することから凝固温度の低いトルエ
ン（′ｍｍ湿温度：１７８Ｋ等の有機熱媒体が使われて
いる。Conventionally, regarding space solar power generation systems, Nis.N.Y., No. 859220 (1985) No. 1.228
Section 1.245 (SAE, No. 859220 (1)
985) Ppl, 228-1.245). In the same document, the Rankine engine is considered to be a promising heat engine for space solar power generation systems. As the circulating heat medium for the Rankine engine, an organic heat medium such as toluene ('mm humidity temperature: 178K), which has a low solidification temperature, is used because it is used in the extremely low temperature of outer space.
有機熱媒体は凝固温度は低いが、高温では分解して非凝
縮性ガスを発生する。そのため上記従来技術では、循環
熱媒体の最高温度を７００〜８００に以下としている。Organic heat carriers have a low solidification temperature, but decompose at high temperatures and generate non-condensable gases. Therefore, in the above-mentioned conventional technology, the maximum temperature of the circulating heat medium is set to 700 to 800 degrees Celsius or less.
そのため、ランキンエンジンの効率が制限され、システ
ムの発電効率を高めることが困難であるという問題があ
った。Therefore, there was a problem in that the efficiency of the Rankine engine was limited and it was difficult to increase the power generation efficiency of the system.
したがって、本発明の目的は、循環熱媒体に温度上限が
ある場合でも、発電効率の高い宇宙太陽熱発電システム
を提供することにある。Therefore, an object of the present invention is to provide a space solar power generation system with high power generation efficiency even when the circulating heat medium has a temperature upper limit.
上記の目的は、集光器、受熱器、熱機関等から構成され
る宇宙太陽熱発電システムにおいて、その受熱器の受光
部と除熱部の間に熱電素子を設けることにより達成され
る。The above object is achieved by providing a thermoelectric element between the light receiving part and the heat removal part of the heat receiver in a space solar thermal power generation system composed of a concentrator, a heat receiver, a heat engine, etc.
また、受光部と熱電素子の間又は熱電素子と除熱部の間
に蓄熱器を設けることが好ましい。Further, it is preferable to provide a heat storage device between the light receiving section and the thermoelectric element or between the thermoelectric element and the heat removal section.
受熱器に入射した太陽光は受光部で熱に変換され、受光
部の温度を上昇させる。そのため、受光部と除熱部との
間に温度差が生じ、熱電素子を介して熱が流れる。この
熱の一部は熱電素子により電気に変換され、残りの熱は
除熱部で循環熱媒体を加熱する。これにより循環熱媒体
の使用温度上限以上の温度で集熱可能とし、熱電素子に
生じる温度差によって熱電素子で発電するとともに、除
熱部において循環熱媒体をその使用温度上限以下で加熱
して熱機関を駆動し、発電することにより、システムの
発電効率を高くする。Sunlight that enters the heat receiver is converted into heat at the light receiving section, raising the temperature of the light receiving section. Therefore, a temperature difference occurs between the light receiving section and the heat removal section, and heat flows through the thermoelectric element. A portion of this heat is converted into electricity by the thermoelectric element, and the remaining heat is used to heat the circulating heat medium in the heat removal section. This makes it possible to collect heat at a temperature above the upper limit of the operating temperature of the circulating heat medium, generate electricity with the thermoelectric element due to the temperature difference that occurs in the thermoelectric element, and heat the circulating heat medium at a temperature below the upper limit of its operating temperature in the heat removal section. By driving the engine and generating electricity, the power generation efficiency of the system is increased.
また、受光部と熱電素子の間又は熱電素子と除熱部の間
に蓄熱器を設けることによって、人工衛星が地球などの
影に入って太陽光が一時的に途絶えた場合にも、蓄熱器
からの熱によって熱電素子とランキンサイクルの両方で
発電が行なわれる。In addition, by providing a heat storage device between the light receiving part and the thermoelectric element or between the thermoelectric element and the heat removal part, even if the satellite enters the shadow of the earth and sunlight is temporarily cut off, the heat storage device can be used. Electricity is generated using both the thermoelectric element and the Rankine cycle.
以下、本発明の一実施例を第１図、第２図により説明す
る。第１図は本発明の宇宙太陽熱発電システムの受熱器
構造を示す部分断面図である。第１図に示すように開口
部７を有する空洞状の受熱器１は１円筒状の循環熱媒体
通路３、循環熱媒体通路３の内部に配置されたヒートパ
イプ４とカプセル型の蓄熱器５、循環熱媒体通路３の内
壁に内張すされた熱電素子２、及び受熱器１からの放熱
損失を小さくするための断熱壁６より構成されている。An embodiment of the present invention will be described below with reference to FIGS. 1 and 2. FIG. 1 is a partial sectional view showing the structure of a heat receiver of the space solar power generation system of the present invention. As shown in FIG. 1, a hollow heat receiver 1 having an opening 7 includes a cylindrical circulating heat medium passage 3, a heat pipe 4 disposed inside the circulating heat medium passage 3, and a capsule-shaped heat storage 5. , a thermoelectric element 2 lined on the inner wall of a circulating heat medium passage 3, and a heat insulating wall 6 for reducing heat radiation loss from the heat receiver 1.
循環熱媒体９は循環熱媒体通路３を通過する間に加熱さ
れ蒸発する。The circulating heat medium 9 is heated and evaporated while passing through the circulating heat medium path 3.
第２図は第１図に示した受熱器を用いた本発明の宇宙太
陽熱発電システムのシステム構成図である。第２図にお
いて、受熱器１からの蒸気２１はランキンエンジン２３
．コンデンサー２５、ポンプ２６、再生熱交換器２７を
経て液体２２となって受熱器１に戻る。ランキンエンジ
ン２３には発電機２４が接続され、発電機２４で発電さ
れた電力は電力調整機３０を介して負荷３１に供給され
る。また、熱電素子２で発電された電力は、電力調整機
２８を介して負荷２９に供給される。FIG. 2 is a system configuration diagram of the space solar power generation system of the present invention using the heat receiver shown in FIG. 1. In FIG. 2, steam 21 from the heat receiver 1 is transferred to the Rankine engine 23.
．． It returns to the heat receiver 1 as a liquid 22 through a condenser 25, a pump 26, and a regenerative heat exchanger 27. A generator 24 is connected to the Rankine engine 23, and the electric power generated by the generator 24 is supplied to a load 31 via a power regulator 30. Further, the electric power generated by the thermoelectric element 2 is supplied to a load 29 via a power regulator 28.
第１図の本発明の宇宙太陽熱発電システムの受熱器１に
おいて、集光器１０（第２図に示す。）によって集光さ
れた太陽光８は開口部７より受熱器１に入射し、熱電素
子２の表面で受光されて熱に変換される。これにより熱
電素子２の表面温度が上昇する。そのため、熱電素子２
の表面（受光部）と循環熱媒体通路３の内壁（除熱部）
との間に温度差が生じ、熱電素子２を介して熱が流れる
。In the heat receiver 1 of the space solar thermal power generation system of the present invention shown in FIG. 1, sunlight 8 collected by the concentrator 10 (shown in FIG. 2) enters the heat receiver 1 through the opening 7 and generates thermoelectric power. The light is received on the surface of the element 2 and converted into heat. This increases the surface temperature of the thermoelectric element 2. Therefore, thermoelectric element 2
surface (light receiving part) and the inner wall of the circulating heat medium passage 3 (heat removal part)
A temperature difference occurs between the two, and heat flows through the thermoelectric element 2.
この熱の一部は熱電素子２により電気に変換され、残り
の熱は循環熱媒体通路３の内壁（除熱部）で循環媒体９
を加熱蒸発させる。この蒸気２１は第２図に示すように
ランキンエンジン２３を駆動し、発電機２４によって発
電される。A part of this heat is converted into electricity by the thermoelectric element 2, and the remaining heat is transferred to the circulating medium 9 by the inner wall (heat removal part) of the circulating heat medium passage 3.
Heat and evaporate. This steam 21 drives a Rankine engine 23 as shown in FIG. 2, and is generated by a generator 24.
第３図に、本実施例の宇宙太陽熱発電システムの発電効
率を実線で、従来のランキンエンジン（ランキンサイク
ル）単独時の発電効率を破線で示す。なお、同図横軸の
集光比は集光器１０の開口面積と受光器１の開口部７の
面積の比で定義した。熱電素子２としてＴＰＭ−２１７
を用い、Ｗｉ環熟熱媒体９温度を６７３にとした。また
、熱電素子２の厚みをパラメータとして示した。第３図
より１本発明のシステムの発電効率は、従来のランキン
サイクル単独時の１．１〜１．２倍に向上出来ることが
わかる。熱電素子２としてさらに性能の高いものが使用
出来れば、発電効率をさらに高く出来る。In FIG. 3, the power generation efficiency of the space solar power generation system of this embodiment is shown by a solid line, and the power generation efficiency when the conventional Rankine engine (Rankine cycle) is used alone is shown by a broken line. Note that the light collection ratio on the horizontal axis in the figure is defined as the ratio of the aperture area of the condenser 10 to the area of the aperture 7 of the light receiver 1. TPM-217 as thermoelectric element 2
Using this, the temperature of the Wi ring aging heat medium 9 was set to 673. Moreover, the thickness of the thermoelectric element 2 is shown as a parameter. From FIG. 3, it can be seen that the power generation efficiency of the system of the present invention can be improved by 1.1 to 1.2 times that of the conventional Rankine cycle alone. If a thermoelectric element 2 with higher performance can be used, the power generation efficiency can be further increased.
したがって、本実施例で示したように、熱電素子に生じ
る温度差によって熱電素子で発電するとともに１．除熱
部において循環熱媒体をその使用温度上限以下で加熱蒸
発させてランキンエンジン、発電機で発電できるので、
従来のランキンサイクル単独時に比較して発電効率を大
幅に向上出来る。Therefore, as shown in this embodiment, while the thermoelectric element generates electricity due to the temperature difference generated in the thermoelectric element, 1. In the heat removal section, the circulating heat medium is heated and evaporated below the upper limit of its operating temperature, and the Rankine engine and generator can generate electricity.
Power generation efficiency can be significantly improved compared to the conventional Rankine cycle alone.
本発明の他の実施例を示す受熱器断面図を第４図に示す
。本実施例では空洞状の受熱器４１の内部にヒートパイ
プ４４をリング状に配置し、ヒードパイブ４４の中央部
に蓄熱器４５を、ヒートパイプ４４の凝縮部側４９に熱
電素子４２を設け、熱電素子４２と循環熱媒体通路４３
を伝熱ブロック５０を介して接続している。A sectional view of a heat receiver showing another embodiment of the present invention is shown in FIG. In this embodiment, a heat pipe 44 is arranged in a ring shape inside a hollow heat receiver 41, a heat storage device 45 is provided in the center of the heat pipe 44, and a thermoelectric element 42 is provided on the condensing part side 49 of the heat pipe 44. Element 42 and circulating heat medium path 43
are connected via a heat transfer block 50.
太陽光８はヒートパイプ４４の蒸発部側４８で受光され
、熱はその一部が蓄熱器４５に蓄熱され、残りの熱は熱
電素子４２、伝熱ブロック５ｏを介して循環熱媒体通路
４３を加熱する。これにより、人工衛星が地球などの影
に入って太陽光８が途絶えた場合には、蓄熱器４５から
熱が供給されて、熱電素子４２、伝熱ブロック５０を介
して循環熱媒体通路４３を加熱する。したがって、太陽
光８が一時的に途絶えた場合にも、熱電素子とランキン
サイクルの両方で発電出来るいう効果がある。The sunlight 8 is received by the evaporator side 48 of the heat pipe 44, a part of the heat is stored in the heat storage device 45, and the remaining heat is sent through the circulating heat medium path 43 via the thermoelectric element 42 and the heat transfer block 5o. Heat. As a result, when the artificial satellite enters the shadow of the earth or the like and sunlight 8 is cut off, heat is supplied from the heat storage device 45 and circulates through the heat transfer medium path 43 via the thermoelectric element 42 and the heat transfer block 50. Heat. Therefore, even if sunlight 8 is temporarily cut off, there is an effect that power can be generated using both the thermoelectric element and the Rankine cycle.
本発明のさらに他の実施例を示す受熱器の断面図を第５
図に示す。本実施例では空洞状の受熱器５１の内部にヒ
ートパイプ５４をリング状に配置し、ヒートパイプ５４
の内部に蓄熱器５５を、ヒートパイプ５４の蒸発部側５
８に熱電素子５２を設け、ヒートパイプ５４の凝縮部側
５９と循環熱媒体通路５３を伝熱ブロック６０を介して
接続している。本実施例では、複数のヒートパイプ５４
の内部に蓄熱器５５を分散して配置しているため、単体
のヒートパイプまたは蓄熱器が破損しても、システム全
体には故障が伝播しないため信頼性を高く出来るという
効果がある。A sectional view of a heat receiver showing still another embodiment of the present invention is shown in FIG.
As shown in the figure. In this embodiment, a heat pipe 54 is arranged in a ring shape inside a hollow heat receiver 51.
A heat storage device 55 is placed inside the heat pipe 54 on the evaporation section side 5.
8 is provided with a thermoelectric element 52, and the condensing section side 59 of the heat pipe 54 and the circulating heat medium passage 53 are connected via a heat transfer block 60. In this embodiment, a plurality of heat pipes 54
Since the heat accumulators 55 are arranged in a distributed manner inside the system, even if a single heat pipe or heat accumulator is damaged, the failure will not propagate to the entire system, which has the effect of increasing reliability.
本発明によれば、循環熱媒体の使用温度上限以上の温度
で集熱可能となり、熱電素子に生じる温度差によって熱
電素子で発電するとともに、除熱部において循環熱媒体
をその使用温度上限以下で加熱して熱機関を駆動し、発
電することができるので、宇宙太陽熱発電システムの発
電効率を熱機関単独時より高く出来るという効果がある
。According to the present invention, it is possible to collect heat at a temperature higher than the upper limit of the operating temperature of the circulating heat medium, generate electricity with the thermoelectric element due to the temperature difference generated in the thermoelectric element, and collect the circulating heat medium at a temperature lower than the upper limit of the operating temperature of the circulating heat medium in the heat removal section. Since it can be heated to drive a heat engine and generate electricity, it has the effect of making the power generation efficiency of the space solar power generation system higher than when using only a heat engine.
また、受光部と熱電素子の間又は熱電素子と除熱部の間
に蓄熱器を設けることによって、人工衛星が地球などの
影に入って太陽光が一時的に途絶えた場合にも、熱電素
子とランキンサイクルの両方で発電出来るいう効果があ
る。In addition, by providing a heat storage device between the light receiving part and the thermoelectric element or between the thermoelectric element and the heat removal part, even if the artificial satellite enters the shadow of the earth etc. and sunlight is temporarily cut off, the thermoelectric element It has the advantage of being able to generate electricity using both the Rankine cycle and the Rankine cycle.
第１図は本発明の宇宙太陽熱発電システムの受熱器構造
を示す部分断面図、第２図は第１図に示した受熱器を用
いた本発明の宇宙太陽熱発電システムのシステム構成図
、第３図は本発明の効果を示す説明図、第４図は本発明
の他の実施例を示す受熱器の断面図、第５図は本発明の
さらに他の実施例を示す受熱器の断面図である。
１・・・受熱器、 ２・・・熱電素子、 ３・・・循環
熱媒体通路、 ４・・・ヒートパイプ、 ５・・・蓄熱
器。FIG. 1 is a partial cross-sectional view showing the structure of a heat receiver of the space solar power generation system of the present invention, FIG. 2 is a system configuration diagram of the space solar power generation system of the present invention using the heat receiver shown in FIG. 1, and FIG. 4 is a cross-sectional view of a heat receiver showing another embodiment of the present invention, and FIG. 5 is a cross-sectional view of a heat receiver showing still another embodiment of the present invention. be. DESCRIPTION OF SYMBOLS 1... Heat receiver, 2... Thermoelectric element, 3... Circulating heat medium path, 4... Heat pipe, 5... Heat storage device.
Claims (1)
発電システムにおいて、その受熱器の受光部と除熱部の
間に熱電素子を設けたことを特徴とする宇宙太陽熱発電
システム。２、特許請求の範囲第１項において、該受光
部と該熱電素子の間に蓄熱器を設けたことを特徴とする
宇宙太陽熱発電システム。 ３、特許請求の範囲第１項において、該熱電素子と該除
熱部の間に蓄熱器を設けたことを特徴とする宇宙太陽熱
発電システム。[Claims] 1. A space solar power generation system comprising a concentrator, a heat receiver, and a heat engine, characterized in that a thermoelectric element is provided between the light receiving part and the heat removal part of the heat receiver. Space solar power generation system. 2. The space solar thermal power generation system according to claim 1, characterized in that a heat storage device is provided between the light receiving section and the thermoelectric element. 3. A space solar power generation system according to claim 1, characterized in that a heat storage device is provided between the thermoelectric element and the heat removal section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63010723A JPH01190274A (en) | 1988-01-22 | 1988-01-22 | Space solar power generation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63010723A JPH01190274A (en) | 1988-01-22 | 1988-01-22 | Space solar power generation system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH01190274A true JPH01190274A (en) | 1989-07-31 |
Family
ID=11758205
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP63010723A Pending JPH01190274A (en) | 1988-01-22 | 1988-01-22 | Space solar power generation system |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH01190274A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009147651A3 (en) * | 2008-06-06 | 2010-11-18 | Xelos S.R.L. | A solar energy generator |
| GB2486210A (en) * | 2010-12-06 | 2012-06-13 | Alstom Technology Ltd | Solar receiver comprising an aperture admitting radiation into a cylindrical cavity |
| WO2012076347A3 (en) * | 2010-12-06 | 2013-05-10 | Alstom Technology Ltd. | Improved solar receiver |
| JP2013098494A (en) * | 2011-11-04 | 2013-05-20 | Toshiba Corp | Thermal power generation system |
| CN104272035A (en) * | 2012-04-26 | 2015-01-07 | 斯坦陵布什大学 | Tower Solar Receiver |
| JP2016533955A (en) * | 2013-08-19 | 2016-11-04 | ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ | Method for recovering waste energy from a bleed duct |
-
1988
- 1988-01-22 JP JP63010723A patent/JPH01190274A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009147651A3 (en) * | 2008-06-06 | 2010-11-18 | Xelos S.R.L. | A solar energy generator |
| GB2486210A (en) * | 2010-12-06 | 2012-06-13 | Alstom Technology Ltd | Solar receiver comprising an aperture admitting radiation into a cylindrical cavity |
| WO2012076347A3 (en) * | 2010-12-06 | 2013-05-10 | Alstom Technology Ltd. | Improved solar receiver |
| US9869302B2 (en) | 2010-12-06 | 2018-01-16 | General Electric Technology Gmbh | Solar receiver |
| JP2013098494A (en) * | 2011-11-04 | 2013-05-20 | Toshiba Corp | Thermal power generation system |
| CN104272035A (en) * | 2012-04-26 | 2015-01-07 | 斯坦陵布什大学 | Tower Solar Receiver |
| JP2016533955A (en) * | 2013-08-19 | 2016-11-04 | ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ | Method for recovering waste energy from a bleed duct |
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