JP2006189029A - 層間強度を向上させるために非被覆繊維を組み込んだSiC/SiC複合材 - Google Patents
層間強度を向上させるために非被覆繊維を組み込んだSiC/SiC複合材 Download PDFInfo
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- JP2006189029A JP2006189029A JP2005307937A JP2005307937A JP2006189029A JP 2006189029 A JP2006189029 A JP 2006189029A JP 2005307937 A JP2005307937 A JP 2005307937A JP 2005307937 A JP2005307937 A JP 2005307937A JP 2006189029 A JP2006189029 A JP 2006189029A
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- 239000000463 material Substances 0.000 title abstract description 17
- 239000011184 SiC–SiC matrix composite Substances 0.000 title 1
- 239000011153 ceramic matrix composite Substances 0.000 claims abstract description 32
- 239000010410 layer Substances 0.000 claims description 62
- 238000000576 coating method Methods 0.000 claims description 32
- 229910052710 silicon Inorganic materials 0.000 claims description 28
- 239000011248 coating agent Substances 0.000 claims description 27
- 239000010703 silicon Substances 0.000 claims description 25
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 25
- 239000000919 ceramic Substances 0.000 claims description 22
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 22
- 239000011229 interlayer Substances 0.000 claims description 16
- 239000011159 matrix material Substances 0.000 claims description 16
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 15
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- 238000000034 method Methods 0.000 abstract description 35
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- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 19
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- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
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- Ceramic Products (AREA)
Abstract
【解決手段】本構成部品(10)は、正常エンジン作動時に予測高層間応力の領域(20)を有する。本構成部品(10)は、互いに予め選択した形態に配置された被覆繊維トウ(2)と非被覆繊維トウ(6)との両方を含み、非被覆繊維トウ(6)は、所定の予測高層間応力の領域(20)に設置される。本発明はさらに、エンジン作動時に予測高層間応力の領域(20)を有する複合材タービンエンジン構成部品(10)のようなCMCを製造する方法を含む。
【選択図】 図3
Description
Corporationの登録商標であるSYLRAMIC(商標)繊維が含まれる。「繊維性材料」には、繊維、フィラメント、ストランド、バンドル、ウィスカ、クロス、フェルト及びそれらの組み合わせが含まれる。繊維は一般的に、連続しているが、寸断することもできる。
皮膜の各層は、低温バッチ法ではなく比較的高温連続又は半連続法を用いて堆積される。例えば、好ましい実施態様では、皮膜の各層は、約1400℃(2550°F)〜約1500℃(2730°F)の範囲の温度で堆積される。皮膜の各層について、繊維トウが化学蒸着(CVD)反応装置を通して引張られ、SiC繊維トウがCVD反応装置を通過するとき、皮膜の各層が各SiC繊維トウ上に個別に連続的に堆積される。例示的なCVD法は、参考文献として本明細書に組み入れられている、特願2005−279268号に開示されかつ記載されている。各皮膜層の滞留時間は、約40秒〜約60秒の範囲内であるのが好ましい。この好ましい実施態様では、約2.5時間でトウの約125mを被覆することができる。被覆処理は、1つの層が堆積された後に直ちに別の層が堆積されるように完全に連続的とすることができ、トウは、CVD反応装置の1つのセクションからCVD反応装置の第2のセクションへと通過し、又はそれに代えて半連続操作の場合には同一セクションを通過して戻るようになる。被覆処理は、トウがリールから巻き戻され、各層用のCVD反応装置を通り、次に別のリール上に置かれるように引張られて、次の皮膜層用の同一又は異なるCVD反応装置通って移動して戻されるように、段階的に連続的なものとすることができる。各個々のトウ、より具体的には各トウ内部の各個々の繊維は、従来技術のスラリー鋳造MI法におけるようにクロスを組立てた後に被覆するのではなく、トウを移動させることによって本発明の4つの層皮膜で被覆されるので、各トウへの皮膜は、より均一である。この均一性により、例えばトウ内部の「キャンド(canned)」気孔(トウ内気孔)の発生、並びにプライ内部及びプライ間の特に0.20インチを超える部分厚さのような不均一性の発生などの、物品全体を被覆する場合に固有の多くの問題が回避される。
4 間質セラミックマトリックス
6 非被覆繊維トウ
10 航空機エンジンLPTブレード
12 翼形部
14 ダブテール
16 フィレット半径
18 低層間応力領域
20 高層間応力領域
Claims (10)
- 予測高層間応力の領域と予測低層間応力の領域とを含み、
複数のセラミック繊維トウと、
化学蒸着によって堆積された複数の層を含み、前記セラミック繊維トウの一部分に施されて、少なくとも前記予測低層間応力の領域内に設置された複数の被覆繊維トウを形成する皮膜と、
少なくとも前記予測高層間応力の領域内に設置された複数の非被覆トウと、
前記複数のセラミック繊維トウ間の間質領域内に位置するセラミックマトリックス材料と、をさらに含む、
セラミックマトリックス複合材タービンエンジン構成部品。 - 前記セラミックマトリックス材料が炭化ケイ素である、請求項1記載のセラミックマトリックス複合材タービンエンジン構成部品。
- 前記皮膜が複数の層を含み、前記複数の層が、
BNを含む層と、
前記BNの層の上にあるB(Si)Nを含む層と、
前記B(Si)Nの層の上にあるSi3N4を含む層と、
前記Si3N4の層の上にある炭素を含む層と、を含む、
請求項1記載のセラミックマトリックス複合材タービンエンジン構成部品。 - 前記BNを含む層が約0.25μm〜約0.75μmの厚さであり、前記B(Si)Nを含む層が約0.25μm〜約0.75μmの厚さであり、前記Si3N4を含む層が約0.75μm〜約1.25μmの厚さであり、また前記炭素を含む層が約0.05μm〜約3μmの厚さである、請求項4記載の構成部品。
- 前記BNを含む層がBNから成り、前記B(Si)Nを含む層がB(Si)Nから成り、また前記Si3N4を含む層がSi3N4から成る、請求項4記載の構成部品。
- 前記B(Si)Nを含む層が、約5重量%のシリコン〜約40重量%のシリコンを含む、請求項4記載の構成部品。
- 前記B(Si)Nを含む層が、約5重量%のシリコン〜約25重量%のシリコンを含む、請求項4記載の構成部品。
- 前記B(Si)Nを含む層が、約11重量%のシリコン〜約19重量%のシリコンを含む、請求項4記載の構成部品。
- 前記炭素を含む層が、熱分解炭素として堆積されている、請求項4の構成部品。
- 該構成部品が、容積で繊維が約30%よりも少ない、請求項1記載のセラミックマトリックス複合材タービンエンジン構成部品。
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