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公开(公告)号：US20240060429A1
公开(公告)日：2024-02-22
申请号：US17889542
申请日：2022-08-17
Applicant: General Electric Company
Inventor： Stephan Priebe , Giridhar Jothiprasad , Joseph Capozzi , Thomas Malkus , Michael Macrorie , Trevor H. Wood
CPC classification number: F01D25/24 , F02C3/04 , F01D9/041 , F05D2230/60 , F05D2220/323
Abstract: A turbomachine for an aircraft is provided. The turbomachine includes a plurality of radially-extending blades and an annular endwall opposite the radially-extending blades. The endwall includes an endwall treatment recessed into the endwall. The endwall treatment is characterized by a casing treatment volume compressibility factor (CTVCF), and a casing treatment normalized volume (CTNV), and a blade tip Mach number (Mtip).
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公开(公告)号：US20230417155A1
公开(公告)日：2023-12-28
申请号：US17850582
申请日：2022-06-27
Applicant: General Electric Company
Inventor： Thomas Malkus , Giridhar Jothiprasad , Christopher E. LaMaster , Jeffrey D. Carnes
IPC: F01D17/14
CPC classification number: F01D17/145 , F05D2260/606
Abstract: Compact bleed valve assemblies are disclosed. An example turbine engine comprises a rotor blade having an axial chord (C) measured at a tip of the rotor blade, and a variable bleed valve (VBV) including a VBV port defining a bleed flowpath and an exit angle (βexit) for bleed air exiting the VBV port, the VBV port including a forward entrance edge and an aft exit edge and a first length (LA) therebetween, and a VBV door corresponding to the VBV port, the VBV door to generate a bleed cavity having a bleed cavity area (BA) in the VBV port when the VBV is in a closed position, the VBV door to move between an open position and the closed position at a rotation angle (Δθ), the VBV door to extend a distance (LAact) beyond the first length (LA), wherein
L
A
+
L
A
a
c
t
C
-
2
*
(
B
V
I
P
+
0
.
1
5
)
-
1
.
3
5
≤
-
0.8
,
and wherein
B
V
I
P
=
0
.
1
5
*
B
A
C
2
+
0
.
8
5
*
Δ
θ
+
β
e
x
i
t
2
π
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公开(公告)号：US20240426247A1
公开(公告)日：2024-12-26
申请号：US18824999
申请日：2024-09-05
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Ramakrishna Venkata Mallina , Giridhar Jothiprasad , Kishore Ramakrishnan , Thomas Malkus
Abstract: A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.
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公开(公告)号：US20230358181A1
公开(公告)日：2023-11-09
申请号：US18353741
申请日：2023-07-17
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor H. Wood , Giridhar Jothiprasad , Nageswar Ganji , Hiranya Kumar Nath , Ravindra Shankar Ganiger , Ambika Shivamurthy
CPC classification number: F02C9/18 , F01D17/105 , F04D27/0215 , F04D27/023 , F02C7/052 , F05D2250/42
Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.
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公开(公告)号：US11739698B2
公开(公告)日：2023-08-29
申请号：US17684172
申请日：2022-03-01
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor H. Wood , Giridhar Jothiprasad , Nageswar Ganji , Hiranya Kumar Nath , Ravindra Shankar Ganiger , Ambika Shivamurthy
CPC classification number: F02C9/18 , F01D17/105 , F02C7/052 , F04D27/023 , F04D27/0215 , F05D2250/42
Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.
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Patent Agency Ranking
公开(公告)号：US20230228220A1
公开(公告)日：2023-07-20
申请号：US17684172
申请日：2022-03-01
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor H. Wood , Giridhar Jothiprasad , Nageswar Ganji , Hiranya Kumar Nath , Ravindra Shankar Ganiger , Ambika Shivamurthy
CPC classification number: F02C9/18 , F01D17/105 , F02C7/052 , F04D27/0215 , F04D27/023 , F05D2250/42
Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.
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公开(公告)号：US12180897B2
公开(公告)日：2024-12-31
申请号：US18353741
申请日：2023-07-17
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor H. Wood , Giridhar Jothiprasad , Nageswar Ganji , Hiranya Kumar Nath , Ravindra Shankar Ganiger , Ambika Shivamurthy
Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.
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公开(公告)号：US12104535B2
公开(公告)日：2024-10-01
申请号：US17717402
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Gregory Alexander Natsui , Giridhar Jothiprasad , Lana Maria Osusky , Thomas Malkus
CPC classification number: F02C7/18 , F01D25/12 , F02C7/141 , F05D2220/32 , F05D2260/213
Abstract: A thermal management system for a gas turbine engine is provided. The gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath; and a thermal management system comprising a supercritical carbon dioxide line thermally coupled to, or integrated into, a portion of the compressor section.
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公开(公告)号：US20240309828A1
公开(公告)日：2024-09-19
申请号：US18182613
申请日：2023-03-13
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor Howard Wood , Kishore Ramakrishnan
IPC: F02K1/06
CPC classification number: F02K1/06
Abstract: A propulsor is provided having a power source; a fan section coupled to the power source and configured to provide thrust opposite a downstream direction; and a cowl assembly at least partially enclosing the power source and the fan section, the cowl assembly including: a forward cowl component; a first aft cowl component disposed in the downstream direction relative to the forward cowl component and movable to vary a first aft cowl displacement from the forward cowl component in the downstream direction; and a second aft cowl component disposed in the downstream direction relative to the first aft cowl component and movable to vary a second aft cowl intermediate displacement from the first aft cowl component.
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公开(公告)号：US20240060510A1
公开(公告)日：2024-02-22
申请号：US18234055
申请日：2023-08-15
Applicant: General Electric Company
Inventor： Stephan Priebe , Giridhar Jothiprasad , Joseph Capozzi , Thomas Malkus , Michael Macrorie , Trevor H. Wood
CPC classification number: F04D29/526 , F04D29/324
Abstract: A turbomachine for an aircraft is provided. The turbomachine includes a plurality of radially-extending blades and an annular endwall opposite the radially-extending blades. The endwall includes an endwall treatment recessed into the endwall. The endwall treatment is characterized by a casing treatment volume compressibility factor (CTVCF), and a casing treatment normalized volume (CTNV), and a blade tip Mach number (Mtip).
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