公开(公告)号：JPH11324615A

公开(公告)日：1999-11-26

申请号：JP11186099

申请日：1999-04-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COSTA MARK W ,  FOOSE ANDREW S ,  KORN NATHAN D ,  KOWZA JAN B ,  LOPARDI WENDY P ,  WELCH DOUGLAS A

IPC: F01D21/04 ,  F01D25/24 ,  F02C7/04

Abstract: PROBLEM TO BE SOLVED: To provide an invasion-resistant fan casing for a turbine engine. SOLUTION: Broken pieces separated from a fan blade 16 are housed by a fan casing 12 for a turbine engine of invasion resistance property. The casing is provided with a supporting body case 14 invaded easily, and an invasion enable cover 32 for enclosing a shock region 1 of a supporting body cover 34 and which is offset from the shock region. A housing cover 36 encloses both of the invasion enable cover 32 and the supporting body cover 34. The housing cover 36 is formed as aromatic polyamide fiber woven fabric, and the supporting body cover 34 is formed as aggregate cell alley.

公开(公告)号：JPH11132004A

公开(公告)日：1999-05-18

申请号：JP24789398

申请日：1998-09-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SAMIT MARC ,  WELCH DOUGLAS A ,  DUESLER PAUL W ,  MARKHAM PATRICK D ,  PENDA ALLAN R

IPC: F01D5/14 ,  F01D5/18 ,  F02K3/04

Abstract: PROBLEM TO BE SOLVED: To keep a danger of damage of a following blade to a minimum in the case where a break off hollow fan blade comes into collision with the following blade. SOLUTION: A hollow air foil for gas-turbine engine having a leading edge 50, a trailing edge 52, a positive pressure face 54 and a negative pressure face 56 comprises a solid region 78 in which a thickness of a blade chord is increased, and a plurality of buttresses 82, 84, 86, 88. The hollow air foil for gas-turbine engine is selectively strengthened. Accordingly, a danger of breakage of the air foil is reduced in a case where the air foil comes into collision with a following air foil when the air foil is in a braking state.

公开(公告)号：DE69817065D1

公开(公告)日：2003-09-18

申请号：DE69817065

申请日：1998-04-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZIPPS ROBERT H ,  SPAULDING REGINALD H ,  TODD EDWARD S ,  KASPROW ROBERT F ,  KLAPPROTH HERMAN C ,  WELCH DOUGLAS A ,  KURZ PHYLLIS L ,  CAFASSO JOSEPH J

IPC: F02C7/04 ,  F01D5/14 ,  F01D21/04 ,  F04D29/08 ,  F04D29/38

公开(公告)号：DE69931554D1

公开(公告)日：2006-07-06

申请号：DE69931554

申请日：1999-04-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COSTA MARK W ,  FOOSE ANDREW S ,  KORN NATHAN D ,  KOWZA JAN B ,  LOPARDI WENDY P ,  WELCH DOUGLAS A

IPC: F01D25/24 ,  F01D21/04 ,  F02C7/04 ,  F02K3/04

Abstract: A penetration resistant turbine engine fan casing (12) for containing separated fragments of a fan blade (16) includes a penetration susceptible support case (14), a penetrable covering (32) circumscribing an impact zone (I) of the support case and an optional collapsible support covering (34) circumscribing the case but axially offset from the impact zone. A containment covering (36) circumscribes both the penetrable covering (32) and the support covering (34). In a preferred embodiment, the coverings are aromatic polyamide fiber fabrics and the support covering is a collapsible cellular array. In operation, a detached fragment of a fan blade penetrates through the case (14) and the penetrable covering (32), and is plastically deformed by the penetrable covering to reduce the fragment's potential for damaging the containment covering (36). The containment covering intercepts the deformed fragment, confining it to a predetermined radial envelope bounded by the inner surface (58) of a nacelle (52). The impact forces arising from a separated blade fragment cause the containment fabric to collapse the cellular array (32) and momentarily detension the containment fabric to maximize its penetration resistance.

公开(公告)号：GB2282856B

公开(公告)日：1998-05-13

申请号：GB9420419

申请日：1994-10-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FRELING MELVIN ,  GRUVER GARY A ,  PARKOS JR JOSEPH JOHN ,  WELCH DOUGLAS A

IPC: F01D5/20 ,  F01D5/28 ,  F01D5/14 ,  F04D29/02 ,  F04D29/08 ,  F04D29/32 ,  F04D29/38

Abstract: A method and apparatus for increasing blade fatigue strength in a turbine engine. The blades in the turbine engine are configured so as to reduce stress at the tip of the blades during operation of the turbine engine, thus increasing blade fatigue strength. This stress reduction helps to counteract the detrimental effect of abrasive tip coatings on blade fatigue strength. In one embodiment, the tip of the blade is chamfered in order to reduce the stress on the tip of the blade. An abrasive coating is then applied to the tip of the blade to assist the blade in seating into an abradable outer air seal. In another embodiment, an abrasive coating is applied to a center portion of the tip of the blade, with the periphery of the abrasive coating being set back from the opposing surfaces of the blade.

公开(公告)号：FR2711181A1

公开(公告)日：1995-04-21

申请号：FR9412223

申请日：1994-10-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MELVIN FRELING ,  GRUVER GARY A ,  PARKOS JOSEPH J JR ,  WELCH DOUGLAS A

IPC: F01D5/20 ,  F01D5/28 ,  F04D29/02 ,  F04D29/08 ,  F01D5/14 ,  F04D29/32 ,  F04D29/38 ,  F01D11/12

Abstract: A method and apparatus for increasing blade fatigue strength in a turbine engine. The blades in the turbine engine are configured so as to reduce stress at the tip of the blades during operation of the turbine engine, thus increasing blade fatigue strength. This stress reduction helps to counteract the detrimental effect of abrasive tip coatings on blade fatigue strength. In one embodiment, the tip of the blade is chamfered in order to reduce the stress on the tip of the blade. An abrasive coating is then applied to the tip of the blade to assist the blade in seating into an abradable outer air seal. In another embodiment, an abrasive coating is applied to a center portion of the tip of the blade, with the periphery of the abrasive coating being set back from the opposing surfaces of the blade.

公开(公告)号：DE69817065T2

公开(公告)日：2004-04-08

申请号：DE69817065

申请日：1998-04-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZIPPS ROBERT H ,  SPAULDING REGINALD H ,  TODD EDWARD S ,  KASPROW ROBERT F ,  KLAPPROTH HERMAN C ,  WELCH DOUGLAS A ,  KURZ PHYLLIS L ,  CAFASSO JOSEPH J

IPC: F02C7/04 ,  F01D5/14 ,  F01D21/04 ,  F04D29/08 ,  F04D29/38

公开(公告)号：DE4436186C2

公开(公告)日：2001-10-25

申请号：DE4436186

申请日：1994-10-10

Applicant: UNITED TECHNOLOGIES CORP PRATT

Inventor： FRELING MELVIN ,  GRUVER GARY A ,  PARKOS JUN JOSEPH J ,  WELCH DOUGLAS A

IPC: F01D5/14 ,  F01D5/20 ,  F01D5/28 ,  F04D29/02 ,  F04D29/08 ,  F04D29/32 ,  F04D29/38

Abstract: A method and apparatus for increasing blade fatigue strength in a turbine engine. The blades in the turbine engine are configured so as to reduce stress at the tip of the blades during operation of the turbine engine, thus increasing blade fatigue strength. This stress reduction helps to counteract the detrimental effect of abrasive tip coatings on blade fatigue strength. In one embodiment, the tip of the blade is chamfered in order to reduce the stress on the tip of the blade. An abrasive coating is then applied to the tip of the blade to assist the blade in seating into an abradable outer air seal. In another embodiment, an abrasive coating is applied to a center portion of the tip of the blade, with the periphery of the abrasive coating being set back from the opposing surfaces of the blade.

公开(公告)号：DE4436186A1

公开(公告)日：1995-05-04

申请号：DE4436186

申请日：1994-10-10

Applicant: UNITED TECHNOLOGIES CORP PRATT

Inventor： FRELING MELVIN ,  GRUVER GARY A ,  PARKOS JUN JOSEPH J ,  WELCH DOUGLAS A

IPC: F01D5/14 ,  F01D5/20 ,  F01D5/28 ,  F04D29/02 ,  F04D29/08 ,  F04D29/32 ,  F04D29/38 ,  F01D5/12 ,  C23C4/10 ,  B23P15/02 ,  B23P9/04 ,  B23P9/02

Abstract: A method and apparatus for increasing blade fatigue strength in a turbine engine. The blades in the turbine engine are configured so as to reduce stress at the tip of the blades during operation of the turbine engine, thus increasing blade fatigue strength. This stress reduction helps to counteract the detrimental effect of abrasive tip coatings on blade fatigue strength. In one embodiment, the tip of the blade is chamfered in order to reduce the stress on the tip of the blade. An abrasive coating is then applied to the tip of the blade to assist the blade in seating into an abradable outer air seal. In another embodiment, an abrasive coating is applied to a center portion of the tip of the blade, with the periphery of the abrasive coating being set back from the opposing surfaces of the blade.

公开(公告)号：DE69931554T2

公开(公告)日：2007-01-18

申请号：DE69931554

申请日：1999-04-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COSTA MARK W ,  FOOSE ANDREW S ,  KORN NATHAN D ,  KOWZA JAN B ,  LOPARDI WENDY P ,  WELCH DOUGLAS A

IPC: F01D25/24 ,  F01D21/04 ,  F02C7/04 ,  F02K3/04

Abstract: A penetration resistant turbine engine fan casing (12) for containing separated fragments of a fan blade (16) includes a penetration susceptible support case (14), a penetrable covering (32) circumscribing an impact zone (I) of the support case and an optional collapsible support covering (34) circumscribing the case but axially offset from the impact zone. A containment covering (36) circumscribes both the penetrable covering (32) and the support covering (34). In a preferred embodiment, the coverings are aromatic polyamide fiber fabrics and the support covering is a collapsible cellular array. In operation, a detached fragment of a fan blade penetrates through the case (14) and the penetrable covering (32), and is plastically deformed by the penetrable covering to reduce the fragment's potential for damaging the containment covering (36). The containment covering intercepts the deformed fragment, confining it to a predetermined radial envelope bounded by the inner surface (58) of a nacelle (52). The impact forces arising from a separated blade fragment cause the containment fabric to collapse the cellular array (32) and momentarily detension the containment fabric to maximize its penetration resistance.