JPS60178904A - Metal panel - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention generally relates to sheet metal panels for gas turbine engines. More particularly, the present invention relates to arcuate panels having small radius bends, particularly arcuate panels in which the bends are substantially perpendicular to the direction of the arc.

The backbone gas turbine engine of the invention has multiple annular sections including a combustor, a high pressure turbine, and a low pressure turbine. Each of these annular areas is bounded by a liner or shroud 1 forming a flow path.

Typical liners and shrouds are suitable for use as supports.
It can be divided into a number of arcuate panels with means for holding it.

Traditionally, such panels have been formed by non-precision casting of parts followed by precision machining. These panels tend to be heavy due to casting constraints requiring a minimum height. These panels also have weaknesses due to air bubbles created during the casting process. Additionally, additional machining time is required, making the panels more expensive.

The panels can also be formed using other manufacturing techniques.

For example, in low pressure turbine blades, multiple sheet metal members may be joined together to form a panel. Again, as with machining, this technique is time consuming and tedious.

OBJECTS OF THE INVENTION It is an object of the present invention to provide a new and improved arcuate sheet metal panel for gas turbine engines.

Another object of the invention is to provide a flow path liner that is much cheaper than previously known.

Yet another object of the present invention is to provide a new and improved arcuate sheet metal shroud for a high pressure turbine.

Oigai! "L [Metal plate for gas turbine engine according to the present invention (5he
(et metal) panel in the stressed area.
J! (hereinafter referred to as stress region). The stress region defines a first arc that intersects the first plane, and defines a second arc that intersects the second plane. The inner radius of the second arc is less than twice the J9 radius of the panel.

In a particular embodiment of the invention, the sheet metal shroud panel comprises:
Arc-shaped shroud backing
), a first wear, and a first rule. A first bar extends outwardly from the backing and extends from the first rule or first wear. The first rule includes first and second portions, the second portion being folded back toward the first portion, thereby forming a stressed region. The stress region defines a first arc that intersects the first plane and defines a second arc that intersects the second plane. The inner radius of the second arc is smaller than the thickness of the panel.

3. Detailed description of the invention Figure 1 shows a route map of a gas turbine engine.

This gas turbine engine 10 includes a compressor 12, a combustor
14, a high pressure turbine 16 and a low pressure turbine 18. The radial boundaries of each of these annular sections are defined by a structure forming a flow path. Compressor 12 is bounded by casing 20, combustor 14 is bounded by liner 22, and turbines 16 and 18
are defined by shrouds 23 and 26, respectively. Each of these structures must be connected to a support. Moreover, for various engineering and assembly reasons, it may be advantageous to divide each structure into a number of arcuate panels. Although the requirements for each of these structures, such as strength, heat resistance, and weight, differ, they all share a common means of strong, reliable, and relatively inexpensive attachment to a support. and is needed.

One embodiment of the present invention is a shroud 2 of a high pressure turbine.
Shroud panel 2 comprising three arcuate segments 1-
It is 4. As shown in Figures 2.3 and 4, the shroud panel 24 is formed from a single sheet of metal. Various materials can be used as the metal plate. Suitable materials consist of high temperature alloys containing the elements nickel, cobalt and chromium, alone or in combination. For example, a material with such characteristics is tl-1astalloy.
X, H8188°L605. Rene'41,
Waspalloy, MA 754 and MA95
It is commercially available as 6. The thickness T of the metal plate depends on the application. In eleven embodiments, the thickness T is greater than or equal to 25 mils, and in preferred embodiments is between 21 J mils and 60 mils.

Shroud panel 24 includes a generally arcuate shroud backing 38 . Its arcuate shape generally conforms to the circumferential shape 40 of the turbine surrounded by the plurality of shroud panels 24. The shroud panel 24 also includes a front mounting structure 42 and an aft mounting drawing 44. The mounting structure shown is for illustrative purposes only, and numerous alternative structures are included within the scope of the present invention. That should be obvious.

As shown in FIG. It includes a first web portion 96 extending outwardly and a second rule portion 98 extending from the first web portion 96.
Attachment element 94 includes a second rail portion 100 and a second web section 102. As will be described in detail below, the first wear member 96 and the rule portion 98 are connected to the second wear member 102.
Element 94 is folded back towards element 92 so as to substantially conform to and second rail portion 100, respectively. Wear members 96 and 102 thus form a web and rail portions 98 and 100 form front rail 30.

Similarly, the rear mounting structure 44 is comprised of a third mounting element 104 and a fourth mounting element 106. 3rd take A” element 104
includes a third web member 108 extending outwardly from the aft end of shroud backing 38;
and a third rail portion 110 extending from 8 . Fourth attachment element 106 includes a fourth rail portion 112 and a fourth web member 114. As in the case of the front mounting structure 42, the rear mounting structure 44 is also configured such that the third web member 108 and the third rail portion 110 are aligned with the fourth web portion 114 and the fourth rail portion 112, respectively. , element 106 is folded back towards element 104. Thus, wear members 108 and 114 form a web and rail portions 110 and 112 form rear rail 32.

To attach each shroud panel 24 to support 28, as shown in FIG. It is done by fitting. In addition to the generally arcuate shape with respect to the circumferential direction 40 of the shroud panel 24, there are bent portions 46a, 46b, 46c, 4 approximately perpendicular to the circumferential direction 40.
6d, 46e, 4Gf, 46g, and 46h are formed. A stress region is formed in the vicinity of each bend where tensile and/or compressive stresses result from both the arc shape and the bends perpendicular to it.

FIG. 5 shows in detail the stress area [48] of the shroud panel 24 near the bent portion 46g. The stress region 48 is located in the first plane 5
2 is determined. The plane 52 is substantially parallel to the surface in contact with the apex 49 of the bent portion 46C.

The radius of arc 50 is the distance to the centerline of the engine.

Stress region 48 further defines a second arc 54 that intersects second plane 56 . In a preferred example, the second plane 56 is the first plane if+
The plane is perpendicular to i52. The arc 54 is an image of the inner surface 59 of the stress region 48 and corresponds to the inner radius of the bend 4G (11. Generally, the radius 64 of the arc 54 is less than twice the thickness T of the shroud panel 24. .Bending portion 46
In the case of Q, since the shroud panel 24 is folded back, the radius 64 of one circular arc 54 is the thickness of the panel 24 (1-)
much smaller than that, close to zero. Since the shroud panel 24 is folded back at the bend 460, the arc 54 extends approximately iso'.

There are various reasons for maintaining a small radius bend in the bent portion 46g. As shown in FIG. 2, the front rail 30 must fit into the front slot 34. Precise dimensional control must be maintained at this interface. As a result, large radius bends that create bulbous ends in the rail 30 interfere with this fit. Moreover, the gap 6G between the rail portions 68 and 70 is brazed. To obtain sufficient strength, the gap 66 must be narrow throughout its length.

In the past, the inner radius 64 of such a bend typically had to be at least twice (21) the thickness of the shroud panel 24 to avoid breakage. In the present invention, a tight bending portion closer to the small pomegranate opening than 21- is realized. Stress is applied to the metal sheet panel by first shaping it into an arc-like shape around its circumference. This applies tensile stress and J1 compressive stress in the circumferential direction to the panel. This arc is maintained while bending the panel in the second direction to form a very small radius arc.

This method creates a biaxial stress state that allows such small radius bends to be achieved.

Although a complete turn of the panel as shown in Figures 2-5 is necessary to form rails 30 and 32, other small radius bends may be required elsewhere in the panel. be done. For example, stress region 72 near bend 46d is shown in FIG. The stress region 72 has a first plane 76 intersecting the first plane 76 .
A circular arc 74 is defined. Stress region 72 defines a second arc 78 that intersects second plane 82 . Arc 78, which corresponds to the inner radius of bend 46d, has a radius 84 that is less than twice the thickness of shroud panel 24 (2T). In the preferred embodiment, radius 84 is approximately 1-1, but smaller radii can be achieved if desired.

Tight bends can be made whenever it is necessary to replicate the contours of a conventional cast panel. For example, by tightening the bent portions 46aJ5 and 46c, the rear slot 3
The surface area of the rear rail 32 in contact with 6 can be increased. By tightening the bends 4.66, the bonding contact area between the web members 108 and the legs 114 of the blade 90 can be increased. As in the case of bend 46g shown in FIG. 4, the radius of the tight bend can be close to zero if desired.

As shown in FIG. 4, mounting elements 92 and 94, as well as drums 104 and 106, respectively! It is desirable that the joints 60J5 and 61, which meet the El, are brazed. One method for brazing these joints is vacuum bonding, specifically described in U.S. Pat.
1984! The 11th advantage is to use the method described in i No. 0.

It will be apparent to those skilled in the art that the invention is not limited to the particular embodiments described and illustrated herein. The invention is not limited to sikorouds for gas turbine engine turbines. Rather, the invention is equally applicable to any arcuate sheet metal panel that negotiates a tight radius bend in a Caster elbow engine.

The dimensions, proportions j5 and drawing relationships shown in the drawings are given by way of example only and should not be taken as actual dimensions or proportions used in the panels of the invention.

Departing from the gist of the present invention, which is limited by the scope of the claims.11!2-! Numerous modifications, variations, and whole or partial equivalents may be employed without reference.

[Brief explanation of drawings]

FIG. 1 is a schematic diagram of a gas turbine. FIG. 2 is a cross-sectional view of a shroud panel and support according to a '1' embodiment of the present invention. 3 is a perspective view of the shroud panel of FIG. 2; FIG. FIG. 4 is a cross-sectional view of the shroud panel of FIG. 2. FIG. 5 is a perspective view of the stress area of the metal sheet panel. FIG. 6 is a perspective view of another stressed area of a sheet metal panel. 24...Shroud panel, 30.32...Rail, 34, 36...Thrower [~, 38...Shroud backing, 40...Circumferential direction, 42.44...Mounting structure, 46
... Bending portion 48 ... Stress region, 50 ... First circular arc, 52 ... First plane, 54 ... Second circular arc, 56 ...
・Second plane, 64...Radius of second arc, 68.70・
...Rail portion, 72...Stress area, 74...First
Arc, 76...first plane, 78...second arc, 82
...Second plane, 84...Radius of second arc, 90...
・Wear, 92, 94...Mounting element, 96.102・
・・Wear member, 98, 100 ・・Rail part, 10
4.106... Mounting element, 108, 114... Wear member, 110.112... Rail portion. Patent Applicant: General Electric Company, District J3 Page 1 Continued 0 Inventor: Harvey Michael Ameriwake Mansor Power, Cincinnati, Ohio, United States; Bayberry Live, 551 Harino United States, Ohio, West φ Chester, Ke Drive, 779 AM

Claims (1)

[Scope of Claims] 1. A metal plate panel having a stress region, wherein the stress region defines a first arc intersecting a first plane and a second arc intersecting a second plane; A metal plate panel for a gas turbine engine, characterized in that the radius of the circular arc is smaller than twice the thickness of the panel. 2. The metal sheet panel of claim 1, wherein the thickness of said panel is greater than 25 mils. 3. The metal plate panel according to claim 1, wherein the second plane is perpendicular to the first plane. 4. The sheet metal panel of claim 3, wherein said second arc extends over approximately 1806 degrees. 5. A sheet metal panel according to claim 4, wherein the radius of said second arc is less than the thickness of said panel and said stress area constitutes a means for attaching said panel to a support. 6. A generally arc-shaped shroud having a front end and a rear end.
a backing; a first web extending outwardly from the backing; and a first rule extending from the first wear, the second rail portion including first and second rail portions; − The second rule is folded back towards the rule portion to form a stress area.
defining a first circular arc in which the stress region intersects the first plane, and defining a second circular arc intersecting the second plane, and determining that the radius of the second circular arc is smaller than the thickness of the panel. The main feature is the metal plate shroud panel for turbine engines. 7. The shroud panel according to claim 6, wherein the first wear forms a first bent portion with respect to the backing, and the inner radius of the first bent portion is less than twice the thickness of the panel. . 8. The first rule forms a second bend in the first web, and the inner radius of the second bend is less than twice the thickness of the panel. shroud panel. 9. 7. The shroud panel of claim 6, wherein said first rule extends generally parallel to said backing. 10. The first web extends from the front end of the backing, and the panel further includes a second web extending outwardly from the back end of the backing, and a second rail extending from the second web. and wherein the second rail includes third and fourth rail portions, the fourth rail portion is folded back toward the third rail portion to form a second stress region, and the second rail portion
Claim 6, wherein the stress region defines a third circular arc intersecting a third plane and a fourth circular arc intersecting a fourth plane, the radius of the fourth circular arc being smaller than the thickness of the panel. panel. 11. A shroud panel for a gas turbine engine formed from a single sheet of metal, the shroud backing having a generally arcuate shape having a forward end and an aft end, and a first nib extending outwardly from the backing. a first web element including a first rule portion extending from the member and the first web portion 1); a second rail portion and a second web member;
The second nib member is folded back toward the first attachment element so that the rail portion substantially matches the first rule portion and the second nib member substantially matches the first web portion (A).
a second attachment element forming a stress region, the first stress region defining a first arc intersecting the first plane, defining a second arc intersecting the second plane; A shroud panel for a gas turbine engine, wherein the radius of the shroud panel is smaller than the thickness of the panel. 12. The first 11 member forms a first bend with respect to the backing, and the inner radius of the first bend is less than twice the thickness of the panel.
Shroud panel as described in section. 13, the first and second rail portions forming a second bend with respect to the first and second web portions;
12. The shroud panel of claim 11, wherein the inside radius of the bend is less than 218 times the thickness of the panel. 14. The schwa panel of claim 11, wherein said first rule portion extends substantially parallel to said backing. 15, the first attachment element extending from the forward end of the backing, the panel generally extending from a No. 33917 member extending outwardly from the back end of the backing and the third web member; a third mounting element including a third rail portion; and a fourth mounting element including a fourth rail portion J5 and a fourth web member; 3 rail portion and the third web member, respectively, to form a second stress region; The shroud panel according to claim 7A11, wherein a third arc intersects with the third plane and a fourth arc intersects with the fourth plane, and the radius of the fourth arc is smaller than the thickness of the panel. 16. The panel of claim 11, wherein said thickness is greater than 25 mils.