RTX Corporation Patente

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A fan blade includes an airfoil with a leading edge and a trailing edge in a chordwise direction, a root and a tip in a spanwise direction; and a sheath (52) with a solid portion (68) to cover the leading edge (56) and first and second flanks (70,70) extending in the chordwise direction to bond to the pressure and suction sides of the airfoil, respectively. The dimensions of the sheath are varied with respect to the spanwise direction of the blade.

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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A support system for an airfoil piece (62) in a gas turbine engine (20) includes first and second support platforms (72a, 78) for supporting the airfoil piece (62) there between. Each of the support platforms (72a, 78) defines a forward support platform side (84a), an aft support platform side (84b), a first support platform circumferential side (84c), a second support platform circumferential side (84d), an airfoil side (84e), and a non-airfoil side (84f). The airfoil side (84e) of at least one of the support platforms (72a, 78) has a radial channel (86) therein for receiving a complementary radial flange (70) of the airfoil piece (62). Each radial channel (86) includes a radial channel first leg portion (86a) extending adjacent the aft support platform side (84b), a radial channel second leg portion (86b) that extends from the radial channel first leg portion (86a) and that curves toward the forward support platform side (84a), and a radial channel third leg portion (86c) that extends from the second leg portion (86b) toward the forward support platform side (84a).

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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A component assembly 100; 200; 300 of a propulsion system 10 includes a component housing 102; 302 having a plenum 104; 304 configured to receive a pressurized gas flow 106; 306 of the propulsion system 10. The component assembly 100; 200; 300 also includes a lug 108; 308A, 308B integrally formed with the component housing 102; 302, a lug base region 110; 310A, 310B including a vent hole 112; 312A, 312B forming a gas path 114; 314A, 314B between the plenum 104; 304 and an interior 116; 316A, 316B of the lug 108; 308A, 308B, and a pin 118; 318. The pin 118; 318 is configured to be positioned within the interior 116; 316A, 316B of the lug 108; 308A, 308B, where a cavity 120; 320A, 320B is formed between an interior surface 122; 322A, 322B of the lug 108; 308A, 308B and an exterior surface 124, 324 of the pin 118; 318 as positioned within the lug 108; 308A, 308B, thereby forming a compressed gas layer 126; 326 to reduce vibration of the pin 118; 318 within the cavity 120; 320A, 320B based on the pressurized gas flow 106; 306 passing from the plenum 104; 304 through the vent hole 112; 312A, 312B into the cavity 120; 320A, 320B.

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A method of preparing a fibrous preform (16) for use in a ceramic matrix composite comprises coiling a serving yarn (12) around a ceramic tow (10) to form a served tow, the serving yarn (12) comprising a polymer material with embedded ceramic particles (14), incorporating the served tow into a woven fabric, the woven fabric comprising a plurality of served tows, and removing the polymer material of the serving yarn (12) such that the embedded ceramic particles (14) remain in the woven fabric.

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A method of additively manufacturing a component is provided. The method includes generating a three-dimensional (3D) model of the component, generating a first heat map of the 3D model which is illustrative of first thermal effects the component is expected to experience during additive manufacturing, generating a second heat map of the 3D model which is illustrative of second thermal effects the component is expected to experience during operational use, updating the 3D model to include 3D heat exchange fin models for reducing each of the first and second thermal effects and updating the 3D model with the 3D heat exchange fin models to include 3D weight reduction cavity models for weight-neutralizing the 3D heat exchange fin models.

A method of manufacturing an (AM) component (100) includes generating a computer-aided design (CAD) model of target AM component (100), and determining a target machining area on the target AM component (100). The target machining area is designated to receive a machining process. The method further comprises determining a witness line region (110, 112, 122) corresponding to the target machining area of the component (100), and performing an AM component build to build the AM component (100) and form a plurality of textured witness lines (120) in the witness line region (110, 112, 122).

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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A rotating seal (401) rotatable about a rotational axis (A) is provided. The rotating seal (401) includes a body (410) having a first surface (411) disposable to face the rotational axis (A) and a second surface (412) disposable to contact with a stationary element (230). The body (410) defines a cooling channel (420) including one or more entrance channels (430) respectively extending from the first surface (411), one or more exit channels (440) and a plenum (450). The plenum (450) extends circumferentially through the body (410) and has a hot side (451) adjacent to the second surface (412). The plenum (450) is fluidly interposed between the one or more entrance channels (430) and the one or more exit channels (440) whereby fluid exiting the one or more entrance channels (430) and entering the plenum (450) impinges against the hot side (451). A method of manufacturing the rotating seal (401) includes the additive manufacturing of the seal body (410).

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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

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Zusammenfassung wird geladen …

A propulsion system for an aircraft includes a core engine that includes a core flow path (C) where a core flow (50) is compressed in a compressor section (24), communicated to a combustor section (30), mixed with a hydrogen-based fuel and ignited to generate a gas flow that is expanded through a turbine section (32). A fuel system (56) is configured to supply a hydrogen based fuel to the combustor (30) through a fuel flow path (62). A condenser (72) is arranged along the core flow path (C) and configured to extract water from the gas flow. An intercooling system (90) receives a portion of water from the condenser (72) for cooling a portion of the core flow (50) at a first location within the compressor section (24). Heated water from the intercooling system (90) is exhausted to a second location within the core flow path (C) downstream of the first location.

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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …