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公开(公告)号：US20230193824A1
公开(公告)日：2023-06-22
申请号：US17553701
申请日：2021-12-16
Inventor： Robert W. Heeter , Christopher D. Hall , Daniel E. Molnar, Jr.
CPC classification number: F02C7/045 , F01D25/243 , B64D2033/0206
Abstract: A gas turbine engine includes a fan case assembly adapted to extend around blades of a fan rotor included in the gas turbine engine. The fan case assembly includes an annular case that extends around an axis, an acoustic panel coupled to the annular case and configured to dampen vibrations and a bolting arrangement that couples the acoustic panel to the annular case.
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2.发明授权公开(公告)号：US12286936B1
公开(公告)日：2025-04-29
申请号：US18660069
申请日：2024-05-09
Inventor： Daniel E. Molnar, Jr. , Robert W. Heeter , Jonathan M. Rivers
Abstract: A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
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3.发明授权公开(公告)号：US12258870B1
公开(公告)日：2025-03-25
申请号：US18600620
申请日：2024-03-08
Inventor： Daniel E. Molnar, Jr. , Robert W. Heeter , Jonathan M. Rivers
Abstract: A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
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4.发明授权公开(公告)号：US12215712B1
公开(公告)日：2025-02-04
申请号：US18660073
申请日：2024-05-09
Inventor： Daniel E. Molnar, Jr. , Robert W. Heeter , Jonathan M. Rivers
Abstract: A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
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公开(公告)号：US12065979B2
公开(公告)日：2024-08-20
申请号：US18088974
申请日：2022-12-27
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Kathryn A. Sontag , Michael G. Meyer
CPC classification number: F02C9/20 , F02C3/06 , F02K3/04 , B64D31/06 , F05D2220/32 , F05D2260/60
Abstract: A gas turbine engine comprises a primary fan and an engine core. The primary fan is mounted for rotation about an axis of the gas turbine engine to provide thrust. The engine core is coupled to the primary fan and configured to drive the primary fan about the axis to cause the fan to push air to provide thrust for the gas turbine engine.
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Patent Agency Ranking
公开(公告)号：US20240209796A1
公开(公告)日：2024-06-27
申请号：US18088994
申请日：2022-12-27
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Kathryn A. Sontag , Michael G. Meyer
CPC classification number: F02C9/20 , F02C3/04 , F02C6/00 , F05D2220/32 , F05D2220/70 , F05D2270/05 , F05D2270/101
Abstract: A gas turbine engine comprises a primary fan and an engine core. The primary fan is mounted for rotation about an axis of the gas turbine engine to provide thrust. The engine core is coupled to the primary fan and configured to drive the primary fan about the axis to cause the fan to push air to provide thrust for the gas turbine engine.
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公开(公告)号：US12012865B2
公开(公告)日：2024-06-18
申请号：US17564455
申请日：2021-12-29
Inventor： Michael Glavicic , Daniel E. Molnar, Jr. , Matthew Jordan , Michael Meyer
CPC classification number: F01D5/16 , C21D9/0068 , C22F1/183 , F05D2240/304 , F05D2260/961 , F05D2300/701
Abstract: Methods for forming a blade for a gas turbine engine include altering the crystallographic texture of the blade in a discrete region relative to the surrounding locations of the blade to minimize flutter and/or mistune the blade by changing the natural frequency response of at least one mode of the blade.
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公开(公告)号：US11591927B1
公开(公告)日：2023-02-28
申请号：US17553702
申请日：2021-12-16
Inventor： Christopher D. Hall , Robert W. Heeter , Daniel E. Molnar, Jr.
Abstract: A fan case assembly is adapted to extend around blades of a fan rotor included in a gas turbine engine. The fan case assembly includes an annular case that extends around an axis, a fan track liner coupled to the annular case and extending circumferentially at least partway about the axis, and a bolting arrangement that couples the fan track liner to the annular case.
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公开(公告)号：US12286930B1
公开(公告)日：2025-04-29
申请号：US18537256
申请日：2023-12-12
Inventor： Robert W. Heeter , Jonathan M. Rivers , Daniel E. Molnar, Jr.
Abstract: A fan case assembly adapted for use with a gas turbine engine includes a fan casing and a bleed air flow control system. The fan casing includes an annular case and a fan track liner coupled with the annular case. The bleed air flow control system is configured to bleed selectively a portion of air flowing through a gas path of the fan case assembly for use as a cooling source in the fan case assembly.
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公开(公告)号：US12078070B1
公开(公告)日：2024-09-03
申请号：US18234656
申请日：2023-08-16
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Jonathan M. Rivers
CPC classification number: F01D17/14 , F01D25/24 , F05D2220/36 , F05D2270/301
Abstract: A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a plenum that that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the plenum and spaced apart circumferentially about the axis.
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