公开(公告)号：US06627126B2

公开(公告)日：2003-09-30

申请号：US09906198

申请日：2001-07-16

Applicant: Wayde R. Schmidt ,  Donald C. Giedt

Inventor： Wayde R. Schmidt ,  Donald C. Giedt

IPC: C01B3100

CPC classification number: C04B35/571 ,  C04B35/565 ,  C04B35/6264 ,  C04B35/806 ,  C04B2235/3839 ,  C04B2235/3843 ,  C04B2235/3847 ,  C04B2235/3891 ,  C04B2235/404 ,  C04B2235/428 ,  C04B2235/483 ,  C04B2235/80

Abstract: A method for preparing a refractory carbide component includes the steps of providing a carbon rich polymer precursor to silicon carbide and excess carbon, determining an amount of excess carbon in the carbon rich polymer precursor, combining the carbon rich polymer precursor with a selected amount of refractory metal to form a precursor/metal mixture, the selected amount being selected so as to provide stoichiometrically equivalent amounts of the excess carbon and the refractory metal, forming the mixture into a preform of a propulsion component, and heating the preform so as to thermally degrade the carbon rich polymer precursor to produce the silicon carbide and the excess carbon, the excess carbon and the refractory metal reacting to form refractory metal carbide and provide the refractory carbide component.

Abstract translation: 制备难熔碳化物组分的方法包括以下步骤：向碳化硅和过量碳提供富含碳的聚合物前体，确定富碳聚合物前体中的过量碳的量，将富含碳的聚合物前体与选定量的耐火材料 金属以形成前体/金属混合物，所选择的量被选择以提供化学计量等效量的过量碳和难熔金属，将混合物形成为推进组分的预成型体，并加热预成型件以使其热降解 富含碳的聚合物前体以产生碳化硅和过量的碳，过量的碳和难熔金属反应形成难熔金属碳化物并提供耐火的碳化物组分。

公开(公告)号：US06341747B1

公开(公告)日：2002-01-29

申请号：US09429386

申请日：1999-10-28

Applicant: Wayde R. Schmidt ,  Harry E. Eaton, Jr.

Inventor： Wayde R. Schmidt ,  Harry E. Eaton, Jr.

IPC: B64C324

CPC classification number: B82Y30/00 ,  B64C11/205 ,  F01D5/288 ,  F04D29/324 ,  F05D2230/90 ,  F05D2240/303 ,  F05D2300/611 ,  Y02T50/672 ,  Y02T50/673

Abstract: The present invention is a nanocomposite layer applied to the leading edge of an airfoil. The nanocomposite is an elastomeric matrix reinforced with nanosized reinforcing particles ranging in size from about 0.5 to 1000 nanometers and preferably ranging in size from about 5 to 100 nanometers. These nanosized reinforcing particles improve the mechanical properties of a pure elastomer. Improving such properties assists the nanocomposite layer in absorbing and dissipating the impact energy caused by the repeated impact of particulate matter, such as sand and rain. Adding the nanosized reinforcing particles to an elastomer allows the nanocomposite to absorb the impact energy over a larger volume in comparison to a pure elastomeric material. The nanocomposite layer is, therefore, capable of withstanding the repeated impact caused by the particulate matter for a greater length of time compared to a pure elastomer. Applying a nanocomposite layer over an aerodynamic member also increases the airfoil's wear resistance. Hence the present invention increases the airfoil's durability, thereby reducing the frequency at which the airfoil may require repair.

Abstract translation: 本发明是应用于翼型的前缘的纳米复合层。 纳米复合材料是由尺寸为约0.5至1000纳米且优选范围为约5至100纳米的纳米尺寸增强颗粒增强的弹性体基体。 这些纳米增强颗粒改善了纯弹性体的机械性能。 改善这种性能有助于纳米复合层吸收和消散由颗粒物质（如沙尘和雨水）的反复冲击引起的冲击能量。 将纳米尺寸增强颗粒加入到弹性体中可使纳米复合材料与纯弹性体材料相比能够吸收较大体积的冲击能量。 因此，与纯弹性体相比，纳米复合材料层能够耐受由颗粒物质引起的更长时间的重复冲击。 在空气动力学构件上施加纳米复合层也增加了翼型的耐磨性。 因此，本发明增加了翼型件的耐用性，从而降低了翼型件可能需要修理的频率。