JP2011509845A - 熱伝導性構造 - Google Patents
熱伝導性構造 Download PDFInfo
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0089—Producing honeycomb structures
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- C22C—ALLOYS
- C22C9/00—Alloys based on copper
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
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- Y10T156/1002—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina
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- 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
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Abstract
Description
本出願は、2008年8月13日に出願された米国特許非仮出願第12/191,208号、および2008年1月11日に出願された米国特許仮出願第61/020,688号に対する優先権を主張するものであり、それらの内容は、参照により本明細書に組み入れられるものとする。
本発明は、概して、熱伝導性構造の分野に関する。詳細には、本発明は、例示的一局面において、熱変形を減少するように適合された熱伝導性構造を提供することを対象とする。
建物、車両、機械装置、および他の建設の工作物の多くの構造要素は、通常、他の領域より高い温度に晒されている領域を含む。例えば、航空機のジェットエンジンでは、エンジンハウジングの内側領域(すなわち、排気口により近いエンジンハウジングの表面)は、通常、外側領域より高い温度に達する。当該温度差は、多くの場合、構造要素の熱伝導性に関連している。
Claims (38)
- 複数のセル壁を含むハニカム構造であって、該セル壁のそれぞれが、
第一の材料からなる第一の波形板と、
第二の材料からなる第二の波形板であって、該波形板は第一の波形板に接着され、かつ、該第二の材料は第一の材料よりも高い熱伝導性を有する材料を含む、第二の波形板と
を含む、ハニカム構造。 - 第一の材料が、金属、高強度金属、インコネル、インコネル−625、およびステンレス鋼からなる群からの材料を含む、請求項1記載のハニカム構造。
- 第二の材料が銅を含む、請求項1記載のハニカム構造。
- 第一の波形板が、約0.002インチの厚さを有する、請求項1記載のハニカム構造。
- 第二の波形板が第一の波形板より厚い、請求項1記載のハニカム構造。
- 各セル壁が第三の材料からなる第三の波形板を含み、該第三の波形板が第二の波形板に接着されている、請求項1記載のハニカム構造。
- 第三の材料が、金属、高強度金属、インコネル、インコネル−625、およびステンレス鋼からなる群からの材料を含む、請求項6記載のハニカム構造。
- 第三の波形板が、約0.002インチの厚さを有する、請求項6記載のハニカム構造。
- 熱伝導性シェブロン内に配置された、請求項1記載のハニカム構造。
- サウンドバッフル内に配置された、請求項1記載のハニカム構造。
- 排気ノズル組立体内に配置された、請求項1記載のハニカム構造。
- 排気プラグ組立体内に配置された、請求項1記載のハニカム構造。
- 熱伝導性フラップ内に配置された、請求項1記載のハニカム構造。
- 複数のセル壁を含むハニカム構造であって、該セル壁のそれぞれが、
第一の材料からなる第一の波形板と、
第二の材料からなる第二の波形板と、
第一の材料および第二の材料より高い熱伝導性を有する第三の材料を含む、第一および第二の波形板に接着されかつその間に配置されたコア板と
を含む、ハニカム構造。 - 第一の材料が、金属、高強度金属、インコネル、インコネル−625、およびステンレス鋼からなる群からの材料を含む、請求項14記載のハニカム構造。
- 第二の材料が、金属、高強度金属、インコネル、インコネル−625、およびステンレス鋼からなる群からの材料を含む、請求項14記載のハニカム構造。
- 第三の材料が銅を含む、請求項14記載のハニカム構造。
- 第一の材料および第二の材料が同じ材料を含む、請求項14記載のハニカム構造。
- 第一の材料および第二の材料が異なる材料を含む、請求項14記載のハニカム構造。
- シェブロン形状のサウンドバッフル内に配置された、請求項14記載のハニカム構造。
- 排気ノズル内に配置された、請求項14記載のハニカム構造。
- 排気プラグ内に配置された、請求項14記載のハニカム構造。
- 収束型フラップ内に配置された、請求項14記載のハニカム構造。
- 発散型フラップ内に配置された、請求項14記載のハニカム構造。
- 複数の波形セル壁と、
該波形セル壁に垂直でかつ波形セル壁の第一の端部に接着された第一の表面と、
該波形セル壁に垂直でかつ波形セル壁の第二の端部に接着された第二の表面と
を含み、
該波形セル壁のそれぞれが、熱を第一の表面から第二の表面へと伝導するように適合されかつそれによって第一の表面の熱変形を減少させる少なくとも1つの層を含む、
構造。 - 熱伝導性シェブロン内に配置された、請求項25記載の構造。
- 排気ノズル内に配置された、請求項25記載の構造。
- 排気プラグ内に配置された、請求項25記載の構造。
- 収束型/発散型フラップ組立体内に配置された、請求項25記載の構造。
- 以下の工程を含む、熱伝導性シェブロンを製造する方法:
第一層と、高熱伝導性材料を含む、第一層に接着した第二層とを含む、複数の帯板を形成する工程、
当該複数の帯板から複数の波形帯板を形成する工程、
複数の波形帯板からハニカム構造を形成する工程、
第一の表面をハニカム構造の第一の側面に接着する工程、および
第二の表面をハニカム構造の第二の側面に接着する工程。 - 複数の波形帯板の少なくとも1つの波形が、六角形の半分を形成する、請求項30記載の方法。
- ハニカム構造が、複数の六角形セルを含む、請求項30記載の方法。
- 複数の帯板が、第二層に接着された第三層をさらに含み、該第二層が第一層と第三層との間に位置している、請求項30記載の方法。
- 以下の工程を含む、熱伝導性シェブロンを利用する方法:
熱伝導性シェブロンを提供する工程であって、ここで該熱伝導性シェブロンが、
複数のセル壁から形成された複数の六角形セルと、
該六角形セルに垂直でかつ該六角形セルの第一の端部に接着された第一の表面と、
該六角形セルに垂直でかつ該六角形セルの第二の端部に接着された第二の表面とを含み、ここで、該セル壁のそれぞれが、熱を第一の表面から第二の表面へと伝達するように適合されることによって第一の表面の熱変形を減少させる少なくとも1つの層を含む、工程、
および
該熱伝導性シェブロンをエンジンに取り付ける工程。 - エンジンからの騒音を減少させるためにエンジンに取り付けられた熱伝導性シェブロンを備えたエンジンを操作する工程をさらに含む、請求項34記載の方法。
- 熱伝導性シェブロンをエンジンに取り付ける工程が、エンジンの排気ノズルに該熱伝導性シェブロンを取り付ける工程を含む、請求項34記載の方法。
- 熱伝導性シェブロンをエンジンに取り付ける工程が、エンジンのターボファンナセルに該熱伝導性シェブロンを取り付ける工程を含む、請求項34記載の方法。
- エンジンがタービンエンジンを具備している、請求項34記載の方法。
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US2068808P | 2008-01-11 | 2008-01-11 | |
US12/191,208 US8671693B2 (en) | 2008-01-11 | 2008-08-13 | Thermally conductive structure |
PCT/US2009/030659 WO2009089491A2 (en) | 2008-01-11 | 2009-01-09 | Thermally conductive structure |
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EP (1) | EP2240317B8 (ja) |
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US8671693B2 (en) | 2014-03-18 |
WO2009089491A2 (en) | 2009-07-16 |
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