Aircraft gas turbine, and rotor blade of aircraft gas turbine

Patent metadata

Field	Value
Publication number	US-11339676-B2
Application number	US-201816761510-A
Country	US
Kind code	B2
Filing date	Dec 4, 2018
Priority date	Dec 28, 2017
Publication date	May 24, 2022
Grant date	May 24, 2022

Abstract

This aircraft gas turbine is provided with a rotor, a rotor blade (24), a casing, a stationary blade (26), and a guide member (53). The rotor blade (24) has fins (43) projecting from the outer peripheral surface (42a) of a rotor blade shroud (42). A stationary blade shroud (51) of the stationary blade (26) forms a cavity (Ct) with at least the rotor blade shroud (42) and the fins (43). The guide member (53) is provided inside the cavity (Ct) and extends inward from the radial outer side, and an inner-side end part (53a) on the radial inner side faces the outer peripheral surface (42a) of the rotor blade shroud (42) with a gap therebetween.

First claim

The invention claimed is:

1. An aircraft gas turbine comprising:
a rotor rotating around an axis;
a rotor blade having a rotor blade main body extending radially outward from the rotor, a rotor blade shroud provided at a tip of the rotor blade main body, and a fin projecting from an outer peripheral surface of the rotor blade shroud;
a casing surrounding an outer periphery of the rotor and the rotor blade and forming a gap with the fin;
a stationary blade having a stationary blade shroud and a stationary blade main body, the stationary blade shroud being fixed to the casing on a downstream side of the rotor blade, a cavity being defined by at least the stationary blade shroud, the rotor blade shroud, and the fin, and the stationary blade main body extending radially inward from the stationary blade shroud; and
a guide member provided in the cavity, extending radially inward, and including an inner-side end part located at an end on a radial inner side of the guide member and facing the outer peripheral surface of the rotor blade shroud with a gap therebetween,
wherein the outer peripheral surface of the rotor blade shroud facing the inner-side end part is formed in parallel with the axis,
wherein the guide member is provided with an inclined portion in which a direction from the inner-side end part of the guide member toward a radially outward end of the guide member is inclined toward the stationary blade in a direction in which the axis extends, and
wherein the axis is closer to the inner-side end part of the guide member than to an inner peripheral surface of the stationary blade shroud.

2. The aircraft gas turbine according to claim 1 , wherein the gap between the inner-side end part and the outer peripheral surface of the rotor blade shroud is formed so as to be larger than the gap between the fin and the casing.

Assignees

• Mitsubishi Heavy Ind Aero Engines Ltd

Inventors

• Fujimura Daigo
• Hase Takaaki
• Hagiwara Hirokazu

Classifications

• F02C7/28

  Arrangement of seals · CPC title

• F01D11/08

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F01D11/02 Primary

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title

• F01D5/225 Primary

  by shrouding · CPC title

• F05D2240/55

  Seals · CPC title