公开(公告)号：EP4411122A3

公开(公告)日：2024-10-09

申请号：EP24156137.2

申请日：2024-02-06

Applicant: RTX Corporation

Inventor： SOBANSKI, Jon Erik ,  SNYDER, Jacob C.

IPC: F02C3/22 ,  F02C3/30 ,  F02K3/062

CPC classification number: F02C3/22 ,  F02C3/305 ,  F02K3/062 ,  F05D2260/21320130101 ,  F05D2260/4031120130101

Abstract: A propulsion system (20) for an aircraft includes a core engine (22) that generates a core gas flow (50), a propulsor section that is driven by the core engine (22) and disposed aft of the core engine (22), a nacelle (26) that surrounds the core engine (22) and the propulsor section, a water recovery system (40) that is disposed in the nacelle (26), an exhaust duct where the core gas flow (50) is directed radially outward from the core engine (22) to the nacelle (26), an evaporator assembly (42) that is in thermal contact with the exhaust duct where water is recovered by the water recovery system (40) and is heated to generate a steam flow (56) that is subsequently communicated to the core engine (22).

公开(公告)号：EP4400699A1

公开(公告)日：2024-07-17

申请号：EP24151726.7

申请日：2024-01-12

Applicant: RTX Corporation

Inventor： SNYDER, Jacob C. ,  SOBANSKI, Jon Erik

IPC: F02C3/30

CPC classification number: F02C3/305 ,  F02C3/30 ,  F02C3/34 ,  F01K21/047 ,  F02C6/18

Abstract: A steam injected turbine engine (20) includes a core engine section that generates a first gas flow (74), a burner (72) where an inlet flow (74) is mixed with fuel (84) and ignited to generate thermal energy, and an evaporator (64) where thermal energy from at least the first gas flow (74) is used to transform water into a first steam flow (70). The first steam flow (70) is injected into a core flow (14) through the core engine (18).

公开(公告)号：EP4462059A1

公开(公告)日：2024-11-13

申请号：EP24175232.8

申请日：2024-05-10

Applicant: RTX Corporation

Inventor： SOBANSKI, Jon Erik ,  SNYDER, Jacob C.

IPC: F28F1/16 ,  F28D7/16 ,  F28F7/02 ,  F28F1/22

Abstract: A heat exchanger assembly (20) includes an inlet manifold (22) that is configured to receive a working fluid (28), a plurality of microtube assemblies (32) that define corresponding plurality passages (34) for the working fluid (28) and an outlet manifold (24) that is configured to exhaust the working fluid (28). The plurality of microtube assemblies (32) include a one-piece unitary structure that has a web portion (46) that extends between at least a first microtube portion (36) and a second microtube portion (38).

公开(公告)号：EP4431715A3

公开(公告)日：2024-10-16

申请号：EP24154836.1

申请日：2024-01-30

Applicant: RTX Corporation

Inventor： SOBANSKI, Jon E. ,  SNYDER, Jacob C. ,  TERWILLIGER, Neil J.

IPC: F02C3/22 ,  F02C3/30 ,  F02C6/18 ,  F02C7/16

Abstract: A turbine engine (20) with an axis (22) includes a fan section (28), a turbine engine core (34), a bypass flowpath (46; 56), a recovery system (110) and a core flowpath (62). The turbine engine core (34) is configured to power the fan section (28). The turbine engine core (34) includes a core compressor section (30), a core combustor section (31) and a core turbine section (32). The bypass flowpath (46; 56) is fluidly coupled with and downstream of the fan section (28). The recovery system (110) includes an evaporator module (114) and a condenser module (115). The condenser module (115) is arranged radially outboard of and axially overlaps the bypass flowpath (46; 56). The core flowpath (62) extends sequentially through the core compressor section (30), the core combustor section (31), the core turbine section (32), the evaporator module (114) and the condenser module (115).

公开(公告)号：EP4481167A1

公开(公告)日：2024-12-25

申请号：EP24172016.8

申请日：2024-04-23

Applicant: RTX Corporation

Inventor： SOBANSKI, Jon E. ,  SNYDER, Jacob C.

IPC: F01D25/32 ,  F02C3/22 ,  F02C3/30

Abstract: A powerplant (10) for an aircraft includes a turbine engine core (26), a recovery system (16) and a flowpath (50). The turbine engine core (26) includes a compressor section (28), a combustor section (29) and a turbine section (30). The recovery system (16) includes a condenser (80) and a flow circuit (82). The flow circuit (82) includes a separator (94) and a treatment device (102). The recovery system (102) is configured to condense water flowing within the flowpath (50) from a gaseous phase to a liquid phase using the condenser. The recovery system (16) is configured to direct the water in the liquid phase from the flowpath (50) into the flow circuit (82) using the separator (94). The recovery system (16) is configured to treat a quantity of the water within the flow circuit (82) using the treatment device (102) to provide treated water. The recovery system (16) is configured to provide a quantity of the treated water to the turbine engine core (26).

公开(公告)号：EP4428478A1

公开(公告)日：2024-09-11

申请号：EP24162445.1

申请日：2024-03-08

Applicant: RTX Corporation

Inventor： SOBANSKI, Jon E. ,  SNYDER, Jacob C.

IPC: F28D7/16 ,  F28F9/013 ,  F28D21/00

CPC classification number: F28D7/1615 ,  F28F9/013 ,  F28F2225/0420130101 ,  F28D2021/002620130101

Abstract: A heat exchanger (20) comprises a flowpath (52) extending longitudinally through a duct (40). The flowpath (52) extends laterally within the duct (40) between a first sidewall (46) and a second sidewall (47). The flowpath (52) extends vertically within the duct (40) between a first manifold wall (48) and a second manifold wall (49). The first manifold wall (48) is configured to form a peripheral boundary of a first manifold plenum (70) outside of the duct (40). The second manifold wall (59) is configured to form a peripheral boundary of a second manifold plenum (72) outside of the duct (40). A plurality of tubes (26) extend vertically across the flowpath (52) and are connected to the first manifold wall (48) and the second manifold wall (49). Each of the tubes (26) has a bore (110) configured to fluidly couple the first manifold plenum (70) to the second manifold plenum (72). The tubes (26) include a first tube (26A) and a second tube (26B). The first tube (26A) is adjacent and angularly offset from the second tube (26B).

公开(公告)号：EP4461943A3

公开(公告)日：2025-01-01

申请号：EP24163037.5

申请日：2024-03-12

Applicant: RTX Corporation

Inventor： SOBANSKI, Jon E. ,  SNYDER, Jacob C.

IPC: F02C7/06 ,  F01D25/16

Abstract: A turbine engine (20) is provided that includes a first rotating assembly (80), a bearing (90D), a turbine engine core (34) and a flowpath (52). The first rotating assembly (80) includes a propulsor rotor (66), a power turbine rotor (67) and a power turbine shaft (78) coupled with and axially between the propulsor rotor (66) and the power turbine rotor (67). The bearing (90D) rotatably supports the first rotating assembly (80) at an intermediate location (102) along the power turbine shaft (78). The turbine engine core (34) includes a second rotating assembly (84, 88) and a combustor (122). The second rotating assembly (84, 88) includes a core compressor rotor (68, 69) and a core turbine rotor (70, 71). The power turbine rotor (67) is arranged axially between the propulsor rotor (66) and the second rotating assembly (84, 88). The flowpath (52) extends sequentially across the core compressor rotor (68, 69), the combustor (122), the core turbine rotor (70, 71) and the power turbine rotor (67) from an inlet (54) into the flowpath (52) to an exhaust (56) from the flowpath (52).

公开(公告)号：EP4461943A2

公开(公告)日：2024-11-13

申请号：EP24163037.5

申请日：2024-03-12

Applicant: RTX Corporation

Inventor： SOBANSKI, Jon E. ,  SNYDER, Jacob C.

IPC: F02C7/06 ,  F01D25/16

Abstract: A turbine engine (20) is provided that includes a first rotating assembly (80), a bearing (90D), a turbine engine core (34) and a flowpath (52). The first rotating assembly (80) includes a propulsor rotor (66), a power turbine rotor (67) and a power turbine shaft (78) coupled with and axially between the propulsor rotor (66) and the power turbine rotor (67). The bearing (90D) rotatably supports the first rotating assembly (80) at an intermediate location (102) along the power turbine shaft (78). The turbine engine core (34) includes a second rotating assembly (84, 88) and a combustor (122). The second rotating assembly (84, 88) includes a core compressor rotor (68, 69) and a core turbine rotor (70, 71). The power turbine rotor (67) is arranged axially between the propulsor rotor (66) and the second rotating assembly (84, 88). The flowpath (52) extends sequentially across the core compressor rotor (68, 69), the combustor (122), the core turbine rotor (70, 71) and the power turbine rotor (67) from an inlet (54) into the flowpath (52) to an exhaust (56) from the flowpath (52).

公开(公告)号：EP4417920A1

公开(公告)日：2024-08-21

申请号：EP24156383.2

申请日：2024-02-07

Applicant: RTX Corporation

Inventor： SNYDER, Jacob C. ,  SOBANSKI, Jon E. ,  WIEDENHOEFER, James F. ,  KIRSCH, Kathryn L.

IPC: F28D1/04

CPC classification number: F28D1/04 ,  F28F2210/0820130101

Abstract: A tube bundle heat exchanger (10) includes a flow space for a first heat exchange medium; and a plurality of heat exchange tubes (38, 40) for a second heat exchange medium, wherein the plurality of heat exchange tubes (38, 40) extends at least partially across the flow space, wherein the plurality of heat exchange tubes (38, 40) comprises at least a first plurality of tubes (38) having a first diameter and a second plurality of tubes (40) having a second diameter different from the first diameter.

公开(公告)号：EP4462061A1

公开(公告)日：2024-11-13

申请号：EP24162986.4

申请日：2024-03-12

Applicant: RTX Corporation

Inventor： SNYDER, Jacob C.

IPC: F28F9/00 ,  F28D9/00

Abstract: An apparatus is provided for an aircraft powerplant. This apparatus includes a heat exchanger (20). The heat exchanger (20) includes a frame (22), a plurality of heat exchanger cores (24), a first flowpath (96) and a second flowpath (98). The frame (22) extends circumferentially about an axis (26). The frame (22) includes a plurality of receptacles (48) within an interior of the frame (22). Each of the heat exchanger cores (24) is housed within a respective one of the receptacles (48). The first flowpath (96) extends in a first direction across the heat exchanger (20) and through the plurality of heat exchanger cores (24). The second flowpath (98) extends in a second direction across the heat exchanger (20) and through the plurality of heat exchanger cores (24).