NOZZLE RING ADHESIVE BONDED BLADING FOR AIRCRAFT ENGINE COMPRESSOR
A compressor nozzle ring for an aircraft includes an inner shroud, an outer shroud and a multiplicity of blades extending from the inner shroud to the outer shroud. Each blade passes through the inner shroud and is attached to it with sealing cement containing an organic polymer adhesive. The adhesive is polyimide based.
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The invention relates to a compressor nozzle ring for an aircraft engine including an inner shroud, an outer shroud, and a multiplicity of blades arranged circumferentially and extending radially from the inner shroud to the outer shroud, each blade passing through a corresponding aperture formed in the inner shroud and being attached to the latter by means of a sealing cement containing an organic polymer adhesive.
Three techniques are currently employed to fix the blades of a nozzle ring to the inner shroud, i.e. mechanical assembly by bolting or riveting, high-temperature soldering using filler metals, and bonding by means of filled silicone elastomers.
By way of example, U.S. Pat. No. 6,431,830 describes a nozzle ring wherein the blades are attached to the inner shroud by high-temperature soldering.
Mechanical solutions are disadvantageous by reason of their high production cost as well as their complexity and weight.
The high-temperature soldering solution is not always applicable depending on the constituent materials of the blades and the shroud. In particular, when these components are made of titanium, high-temperature soldering must be carried out at very high temperatures resulting in prohibitive deformation.
The solution using silicone elastomer is effective, but the service life of these elastomers diminishes when the operating temperature of the compressor increases. Thus, for new generation compressors operating continuously at temperatures in the region of 300° C. in an atmosphere containing oil mist, silicone elastomer based adhesives suffer embrittlement which limits the practical service life to 100 hours.
The object of the invention is to overcome the aforementioned drawbacks of the known fixing methods.
In particular, it is desired to obtain bonded joints that are workable for 1000 hours at temperatures in the region of 300° C.
The invention relates in particular to a nozzle ring of the type described in the introduction, and provides that the adhesive is polyimide-based.
Polyimide-based adhesives provide long-term resistance to the atmospheres obtaining in the compressors of aircraft engines, and it is possible to choose such an adhesive in relation to the specified operating temperature, certain such adhesives being capable of withstanding temperatures in the order of 300° C.
Optional features of the invention, whether complementary or Alternative in character, are described below:
-
- The inner shroud and/or the blades are made of titanium.
- End regions of the blades project radially inward beyond the inner shroud.
- An insert disposed inside the inner shroud and in proximity to the latter delineates in conjunction with the inner shroud and the blades a space that is filled with said cement.
- Said insert takes the form of a flexible sheet.
- At the ends of the blades, the flexible sheet forms pockets extending radially away from the inner shroud.
- The flexible sheet is formed from several elements connected together in the circumferential direction of the inner shroud with partial overlap.
- The flexible sheet is a glass or carbon fibre fabric impregnated with polyimide.
- Said insert takes the form of a multiplicity of rigid parts.
- Each of said rigid parts is interposed between projecting regions of two consecutive blades.
- Each of said rigid parts is force-fitted between said projecting regions.
- Each of said rigid parts extends on a length of arc greater than the circumferential pitch of the blades.
- Said rigid parts present apertures to receive the projecting regions of the blades.
- Said rigid parts are fixed to the inner shroud by means of said cement.
- Said rigid parts are made of aluminium alloy or magnesium alloy.
- Said cement is in film form.
- Said cement is in the form of foam.
- Said polyimide-based adhesive is capable of withstanding a temperature of approximately 300° C. without deterioration during operation of the nozzle ring.
- The blades are fixed to the outer shroud by electron beam welding.
The characteristics and advantages of the invention are set forth in greater detail in the description below with reference to the attached figures.
In a conventional manner, the compressor stage shown in
The way the blades are attached to the inner shroud 1, according to the invention, is described below.
In
To make the attachment illustrated in
In the embodiment in
The attachment in
The method of attachment in
Claims
1. A compressor nozzle ring for an aircraft engine, said nozzle ring comprising:
- an inner shroud;
- an outer shroud; and
- a multiplicity of blades arranged circumferentially and extending radially from the inner shroud to the outer shroud, each of the blades passing through a corresponding aperture formed in the inner shroud and being attached to the inner shroud with sealing cement containing an organic polymer adhesive,
- wherein said adhesive is polyimide based;
- wherein end regions of the blades project radially inward beyond the inner shroud;
- wherein an insert disposed inside the inner shroud and in proximity to the inner shroud surrounds, in conjunction with the inner shroud and the blades, a continuous space along the inside of the inner shroud that is filled with said cement, and the continuous space filled with the cement continues without a gap between adjacent blades of the blades and around the end regions of the adjacent blades; and
- wherein said insert surrounds the end regions of the adjacent blades including a radially innermost area of the adjacent blades.
2. The nozzle ring according to claim 1, wherein the inner shroud and/or the blades are made of titanium.
3. The nozzle ring according to claim 1, wherein said insert is a flexible sheet.
4. The nozzle ring according to claim 3, wherein the flexible sheet forms pockets at the end regions of the adjacent blades, said pockets extending radially away from the inner shroud.
5. The nozzle ring according to claim 4, wherein the flexible sheet is formed from several elements connected together in the circumferential direction of the inner shroud with partial overlap.
6. The nozzle ring according to claim 4, wherein the flexible sheet is a glass fibre or carbon fibre fabric impregnated with polyimide.
7. (canceled)
8. A compressor nozzle ring for an aircraft engine, comprising:
- an inner shroud;
- an outer shroud; and
- a multiplicity of blades arranged circumferentially and extending radially from the inner shroud to the outer shroud, each of the blades passing through a corresponding aperture formed in the inner shroud and being attached to the inner shroud with sealing cement containing an organic polymer adhesive,
- wherein said adhesive is polyimide based;
- wherein end regions of the blades project radially inward beyond the inner shroud;
- wherein an insert disposed inside the inner shroud and in proximity to the inner shroud surrounds, in conjunction with the inner shroud and the blades, a space that is filled with said cement, and the space filled with the cement continues without a gap between adjacent blades of the blades;
- wherein said insert includes a multiplicity of rigid parts; and
- wherein each of said rigid parts is interposed between the end regions of the adjacent blades such that each individual part of said rigid parts covers a side of the end regions of each of the adjacent blades to surround the space that is filled with cement.
9. The nozzle ring according to claim 8, wherein each of said rigid parts is force fitted between said end regions.
10. The nozzle ring according to claim 8, wherein each of said rigid parts extends over a length of arc greater than a circumferential pitch of the adjacent blades.
11. The nozzle ring according to claim 10, wherein said rigid parts have apertures to receive the end regions of the adjacent blades.
12. The nozzle ring according to claim 8, wherein said rigid parts are fixed to the inner shroud by said cement.
13. The nozzle ring according to claim 8, wherein said rigid parts are made of aluminum alloy or magnesium alloy.
14. The nozzle ring according to claim 1, wherein said cement is in film form.
15. The nozzle ring according to claim 1, wherein said cement is in foam form.
16. The nozzle ring according to claim 1, wherein said polyimide-based adhesive is capable of withstanding a temperature of approximately 300° C. without deterioration during operation of the nozzle ring.
17. The nozzle ring according to claim 1, wherein the blades are attached to the outer shroud by electron beam welding.
18. The nozzle ring according to claim 8, wherein said insert has an angled U profile.
19. The nozzle ring according to claim 8, wherein said insert is a non-hollow solid insert.
20-22. (canceled)
23. The nozzle ring according to claim 1, wherein the insert includes a plurality of insert pieces and each of the plurality of insert pieces surrounds the end regions including the radially innermost area of a plurality of the blades.
24. (canceled)
Type: Application
Filed: Sep 20, 2006
Publication Date: Jun 11, 2009
Applicant: SNECMA MOTEURS (Paris)
Inventors: Claude Marcel Mons (Savigny Le Temple), Sandra Andrieu (Roissy-en-Brie), Manuel Girard (Vaux Le Penil), Francois Pierre Ribassin (Villabe)
Application Number: 11/523,522
International Classification: F01D 5/14 (20060101);