-
Patent Agency Ranking
公开(公告)号：US06881036B2
公开(公告)日：2005-04-19
申请号：US10235025
申请日：2002-09-03
Applicant: David Charles Hornick , Frank J. Euvino, Jr. , James Tyler Roach
Inventor： David Charles Hornick , Frank J. Euvino, Jr. , James Tyler Roach
CPC classification number: F01D5/282 , F01D5/225 , F01D5/34 , F04D29/023 , F04D29/321 , F05D2250/15 , F05D2300/43 , F05D2300/603
Abstract: The present invention relates to an integrally bladed rotor for use in a gas turbine engine. The integrally bladed rotor comprises a plurality of pairs of airfoil blades. Each pair of blades has a spar which extends from a first tip of a first one of the airfoil blades in the pair to a second tip of a second one of the airfoil blades in the pair. The rotor further comprises an outer shroud integrally joined to the first and second tips in each pair of airfoil blades and an inner diameter hub.
Abstract translation: 本发明涉及一种用于燃气涡轮发动机的整体叶片转子。 整体叶片转子包括多对翼型叶片。 每对叶片具有翼形件，翼梁从一对翼型叶片的第一叶片的第一端部延伸到一对翼型叶片的第二叶片的第二端部。 转子还包括与每一对翼型叶片中的第一和第二尖端一体地连接的外护罩和内径毂。
-
2.发明授权公开(公告)号：US08703269B2
公开(公告)日：2014-04-22
申请号：US13396325
申请日：2012-02-14
Applicant: John Everett Reighley , David Charles Hornick , Andrew Foose , Charles Owen Aitken , Kevin Andrew Shea
Inventor： John Everett Reighley , David Charles Hornick , Andrew Foose , Charles Owen Aitken , Kevin Andrew Shea
IPC: E04C3/38
CPC classification number: B64C1/12 , B29C66/1122 , B29C66/474 , B29C66/524 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/72143 , B29C66/73751 , B29C66/73752 , B29C66/73755 , B29C66/81455 , B29C70/222 , B29C70/44 , B29D99/0007 , B29D99/0014 , B29L2031/3076 , B64C1/064 , B64C2001/0072 , Y02T50/43 , Y10T428/24174 , Y10T428/24612 , B29K2307/04 , B29K2309/08 , B29K2309/02 , B29K2305/00 , B29K2063/00 , B29K2075/00 , B29K2067/00
Abstract: Embodiments of reinforced composite structures for aircrafts and methods for making such reinforced composite structures are provided herein. A reinforced composite structure for an aircraft comprises a fiber reinforced composite stringer. The fiber reinforced composite stringer comprises a beam body portion and a runout portion that extends from the beam body portion in a first direction. The beam body and runout portions are defined by projection of a variable I-shaped cross-section in the first direction along at least a portion of an entire combined length of the beam body and runout portions. The variable I-shaped cross-section has a cap section, a foot section, and a web section that extends between the cap and foot sections. The variable I-shaped cross-section is configured such that a height of the web section tapers in the first direction along at least a portion of an entire length of the runout portion.
Abstract translation: 本文提供了用于飞机的增强复合结构的实施例和用于制造这种增强复合结构的方法。 用于飞行器的增强复合结构包括纤维增强复合纵梁。 纤维增强复合纵梁包括梁主体部分和从梁本体部分沿第一方向延伸的偏离部分。 沿着梁主体和偏转部分的整个组合长度的至少一部分，沿着第一方向突出可变的I形横截面来限定梁主体和偏转部分。 可变的I形横截面具有盖部分，脚部分和在帽部分和脚部之间延伸的腹板部分。 可变的I形横截面构造成使得腹板部分的高度沿着偏心部分的整个长度的至少一部分在第一方向上逐渐变细。
-
3.发明申请公开(公告)号：US20130209746A1
公开(公告)日：2013-08-15
申请号：US13396325
申请日：2012-02-14
Applicant: John Everett Reighley , David Charles Hornick , Andrew Foose , Charles Owen Aitken , Kevin Andrew Shea
Inventor： John Everett Reighley , David Charles Hornick , Andrew Foose , Charles Owen Aitken , Kevin Andrew Shea
CPC classification number: B64C1/12 , B29C66/1122 , B29C66/474 , B29C66/524 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/72143 , B29C66/73751 , B29C66/73752 , B29C66/73755 , B29C66/81455 , B29C70/222 , B29C70/44 , B29D99/0007 , B29D99/0014 , B29L2031/3076 , B64C1/064 , B64C2001/0072 , Y02T50/43 , Y10T428/24174 , Y10T428/24612 , B29K2307/04 , B29K2309/08 , B29K2309/02 , B29K2305/00 , B29K2063/00 , B29K2075/00 , B29K2067/00
Abstract: Embodiments of reinforced composite structures for aircrafts and methods for making such reinforced composite structures are provided herein. A reinforced composite structure for an aircraft comprises a fiber reinforced composite stringer. The fiber reinforced composite stringer comprises a beam body portion and a runout portion that extends from the beam body portion in a first direction. The beam body and runout portions are defined by projection of a variable I-shaped cross-section in the first direction along at least a portion of an entire combined length of the beam body and runout portions. The variable I-shaped cross-section has a cap section, a foot section, and a web section that extends between the cap and foot sections. The variable I-shaped cross-section is configured such that a height of the web section tapers in the first direction along at least a portion of an entire length of the runout portion.
Abstract translation: 本文提供了用于飞机的增强复合结构的实施例和用于制造这种增强复合结构的方法。 用于飞行器的增强复合结构包括纤维增强复合纵梁。 纤维增强复合纵梁包括梁主体部分和从梁本体部分沿第一方向延伸的偏离部分。 沿着梁主体和偏转部分的整个组合长度的至少一部分，沿着第一方向突出可变的I形横截面来限定梁主体和偏转部分。 可变的I形横截面具有盖部分，脚部分和在帽部分和脚部之间延伸的腹板部分。 可变的I形横截面构造成使得腹板部分的高度沿着偏心部分的整个长度的至少一部分在第一方向上逐渐变细。
-
公开(公告)号：US08413762B1
公开(公告)日：2013-04-09
申请号：US13314954
申请日：2011-12-08
Applicant: Tongan Wang , John Willett Maxon, Jr. , Andrew Foose , David Charles Hornick , Josef Fila
Inventor： Tongan Wang , John Willett Maxon, Jr. , Andrew Foose , David Charles Hornick , Josef Fila
CPC classification number: B64C1/40 , B29C65/00 , B29C66/11 , B29C66/1122 , B29C66/1142 , B29C66/43 , B29K2105/04 , B32B3/12 , B32B5/26 , B32B5/32 , B32B7/02 , B32B2250/02 , B32B2250/03 , B32B2250/04 , B32B2250/05 , B32B2250/20 , B32B2250/22 , B32B2266/0257 , B32B2266/0285 , B32B2266/06 , B32B2307/102 , B32B2307/718 , B32B2605/18 , B64C1/00 , E04B1/82 , E04B1/84 , G10K11/00 , G10K11/02 , Y02T50/46 , Y10T428/24149
Abstract: Embodiments of thermal-acoustic sections for an aircraft for reducing noise along an acoustic path produced from an acoustic source are provided herein. The thermal-acoustic section comprises a first porous layer having a first characteristic acoustic impedance. A second porous layer is disposed adjacent to the first porous layer and has a second characteristic acoustic impedance that is greater than the first characteristic acoustic impedance. The thermal-acoustic section is configured to be positioned along the acoustic path such that at least a portion of the noise from the acoustic source is directed through the first porous layer to the second porous layer to promote absorption of the noise.
-
公开(公告)号：US07284957B2
公开(公告)日：2007-10-23
申请号：US11007503
申请日：2004-12-08
Applicant: David Charles Hornick , Frank J. Euvino, Jr. , James Tyler Roach
Inventor： David Charles Hornick , Frank J. Euvino, Jr. , James Tyler Roach
IPC: F04D5/24
CPC classification number: F01D5/282 , F01D5/225 , F01D5/34 , F04D29/023 , F04D29/321 , F05D2250/15 , F05D2300/43 , F05D2300/603
Abstract: The present invention relates to an integrally bladed rotor for use in a gas turbine engine. The integrally bladed rotor comprises a plurality of pairs of airfoil blades. Each pair of blades has a spar which extends from a first tip of a first one of the airfoil blades in the pair to a second tip of a second one of the airfoil blades in the pair. The rotor further comprises an outer shroud integrally joined to the first and second tips in each pair of airfoil blades and an inner diameter hub.
Abstract translation: 本发明涉及一种用于燃气涡轮发动机的整体叶片转子。 整体叶片转子包括多对翼型叶片。 每对叶片具有翼形件，翼梁从一对翼型叶片的第一叶片的第一端部延伸到一对翼型叶片的第二叶片的第二端部。 转子还包括与每一对翼型叶片中的第一和第二尖端一体地连接的外护罩和内径毂。
-
-
-
-
Search Results
5
records
(took 0.012 seconds)
