Axial-flow thermal turbomachine

• US 7,037,079 B2
• Filed: 03/25/2004
• Issued: 05/02/2006
• Est. Priority Date: 03/26/2003
• Status: Expired due to Term

• Current Assignee: Ansaldo Energia Switzerland AG (Ansaldo Energia SPA)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Nazmy, Mohamed, Gerdes, Claus Paul, Wettstein, Hans
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): HANAN, DEVIN J
• Application Number:
  US10/808,493
• Publication Number:
  US 20060062674A1
• Time in Patent Office: 768 Days
• Field of Search: 416215-218
• US Class Current: 416/215
• CPC Class Codes: F01D 11/008 by spacer elements between the blades, e.g. independent interblade platforms
• CPC Class Codes: F01D 5/02 Blade-carrying members, e.g. rotors rotors of non-bladed type F01D1/34; stators F01D9/00 ; selecting particular materials F01D5/28
• CPC Class Codes: F01D 5/28 Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
• CPC Class Codes: F01D 5/30 Fixing blades to rotors; Blade roots ; Blade spacers
• CPC Class Codes: F05D 2300/50 Intrinsic material properties or characteristics
• CPC Class Codes: F05D 2300/606 Directionally-solidified crystalline structures

Abstract

The invention relates to an axial-flow thermal turbomachine, having a rotor (1) made from a metallic material with a first density (D₁), in which rotor blades (3, 3′) and intermediate pieces (4) are mounted alternately in a circumferential groove. It is characterized in that said intermediate pieces (4) consist of a material with a second density (D₂), which is lower than the first density (D₁). Particularly suitable materials for the intermediate pieces (4) are intermetallic compounds, preferably intermetallic γ-titanium aluminide alloys or intermetallic orthorhombic titanium aluminide alloys, but also titanium alloys.

Claims

1. An axial-flow thermal turbomachine comprising:

a rotor made from a metallic material with a first density (D₁);

a circumferential groove; and

rotor blades and intermediate pieces alternatingly mounted in the circumferential groove;

wherein said intermediate pieces comprise a material with a second density (D₂) lower than the first density (D₁).

2. The turbomachine as claimed in claim 1, wherein the material having the second density (D₂) comprises an intermetallic compound.

3. The turbomachine as claimed in claim 2, wherein said intermetallic compound comprises an alloy selected from the group consisting of a y-titanium aluminide alloy and an orthorhombic titanium aluminide alloy.

4. The turbomachine as claimed in claim 3, wherein said γ

-titanium aluminide alloy has the following chemical composition (in % by weight);

Ti-(30.5–

31.5)Al-(8.9–

9.5)W-(0.3–

0.4)Si.

5. The turbomachine as claimed in claim 1, wherein the material having the second density (D₂) comprises a titanium alloy.

6. The turbomachine as claimed in claim 1, wherein the turbomachine comprises a gas turbine having a high-pressure compressor with a rotor which comprises a stainless Cr—

Ni steel.