Turbinengehäuse- und Dichtungs-Struktur für ein Flugzeugantriebssystem

Details

Veröffentlichungs-Nr.

EP4764162

Anmeldetag

22. Dezember 2025

Veröffentlichung

24. Juni 2026

Rechtsraum

EP

Abstract

A gas turbine engine (22) includes a turbine section (36), a turbine case (70), an inner case (72), and a damping seal baffle (74). The turbine section (36) extends along a rotational axis (50) of the gas turbine engine (22). The turbine case (70) includes a cantilevered inner wall (86). The cantilevered inner wall (86) extends circumferentially about the rotational axis (50). The cantilevered inner wall (86) extends between and to an upstream axial end (88) and a downstream axial end (90). The upstream axial end (88) is disposed at and downstream of the turbine section (36). The cantilevered inner wall (86) forms a seal platform surface (122). The inner case (72) extends circumferentially about the rotational axis (50). The inner case (72) is disposed radially inward of the upstream axial end (88). The damping seal baffle (74) extends circumferentially about the rotational axis (50). The damping seal baffle (74) is mounted to the inner case (72). The damping seal baffle (74) is disposed in contact with the seal platform surface (122).

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada