EP2871368B1 - Gas turbine compressor - Google Patents

Description

The present invention relates to a gas turbine compressor with a Abblaskanal and a gas turbine, in particular aircraft engine gas turbine with such a gas turbine compressor.

For example, from the DE 40 38 353 A1 . DE 199 40 020 C2 and US 2004/0033133 A1 Abblaskanäle are known with straight, against the rotational axis of the compressor constantly inclined downstream channel walls.

The DE 10 2008 014 957 A1 indicates an entrance angle of a flow into a take-off geometry in response to a bleed air amount relative to an amount of air entering a compressor and a hub ratio.

The GB 2 388 875 A suggests a curved upstream channel wall. An axially opposed downstream channel wall has two planar sections connected by a radius. Parameter values for a geometry do not take them into focus.

The EP 2 110 559 A2 In one embodiment, there is shown a downstream channel wall having two planar sections. It does not take parameter values for a channel geometry into account.

The GB 2 192 229 A refers to a ratio of a withdrawal air quantity relative to an amount of air flowing through a compressor in the range between 7 and 10%.

An object of an embodiment of the present invention is to provide an improved gas turbine compressor.

This object is solved by the features of claim 1. Claim 8 provides a gas turbine, in particular an aircraft engine gas turbine, with a corresponding gas turbine compressor under protection. Advantageous embodiments of the invention are the subject of the dependent claims.

According to one aspect of the present invention, a gas turbine compressor, in particular an aircraft engine gas turbine, a guide grid having a plurality of circumferentially distributed vanes and a playpens with a plurality of circumferentially distributed blades on.

In one embodiment, the guide grid is arranged upstream of at least one further outlet guide grid, in particular in the flow direction last, or in front of a downstream walkway. In one embodiment, one or more further running and guide gratings can be arranged between the guide grid and the outlet guide grid.

Guiding and playpens are arranged in an annular space, which is intended to be flowed through during operation of a working gas, in particular air. A cross section of the annular space can, at least in sections, converge or, at least substantially, be constant.

A radially outer wall of the annular space merges into an upstream channel wall of a blow-off channel. In one embodiment, the upstream channel wall continuously merges into the radially outer wall. Axially opposite the Abblaskanal on a downstream channel wall with a radially inner leading edge. In one embodiment, the radially inner leading edge is offset radially inwardly from the transition of the upstream channel wall into the radially outer wall. At an end facing away from the annular space, the blow-off channel has a blow-off channel outlet.

The terms upstream and downstream or upstream and downstream refer to the normal flow direction in the operation of the compressor, in particular an axial direction from the guide grid to the playpen or from a compressor inlet to a compressor outlet.

The exhaust duct may be an annular channel in one embodiment, the leading edge extends in the circumferential direction by 360 °. In one embodiment, the leading edge is rounded or has a, in particular constant, radius. In another embodiment, the Abblaskanal on several circumferentially spaced chimneys or separate passages.

The Abblaskanal can communicate at its Abblaskanalaustritt with a, in particular annular, plenum, in particular, continue to continue in operation from the compressor tapped gas, for example for component cooling or the like. In one embodiment, the blow-off channel communicates with an inflow channel, which in turn can communicate with the plenum.

According to one aspect of the present invention, the downstream channel wall in the meridian section with an axis of rotation of the compressor includes an angle which increases in the direction of flow, in particular continuously or continuously, which is referred to below as the first angle. As a result, the bleed flow can be performed loss in one embodiment. Additionally or alternatively, losses of the main flow in the annular space downstream of the leading edge can thereby also be reduced.

In one embodiment, the first angle increases from the leading edge, in particular to a radius of a rounded leading edge, in the direction of flow. As a result, in one embodiment, the bleeding of the flow at the Abblaskanaleintritt be improved.

Additionally or alternatively, the first angle in one embodiment in the flow direction increases monotonously, in particular strictly monotonously. By this is meant in the present case in particular that the first angle at any axial position is at least as large as at any axial position upstream of it (monotone), or that the first angle at any axial position is greater than at each axial Position that is upstream of this (strictly monotone). In other words, in one embodiment, the downstream channel wall is curved in sections or over its entire length. In one embodiment, the downstream channel wall can have an at least substantially constant radius of curvature or an at least substantially constant curvature in sections or over its entire length. In another embodiment, a curvature of the downstream channel wall in sections or over its entire length increase or decrease or decrease or increase their radius of curvature. As a result, the bleed flow can be performed particularly low loss in one embodiment.

In one embodiment, the first angle at the Abblaskanalaustritt greater than 30 °, in particular greater than 40 °. As a result, the bleed flow can be carried out loss in one embodiment.

According to the invention, the upstream channel wall also includes in the meridian section with the axis of rotation an angle which increases in the direction of flow, which is referred to below as the second angle.

In one embodiment, the second angle increases from the transition of the upstream channel wall in the radially outer wall of the annular space in the direction of flow, in a development, the upstream channel wall is tangentially into the radially outer wall.

Additionally or alternatively, the second angle in one embodiment in the flow direction increases monotonously, in particular strictly monotonously. In other words, in one embodiment, the upstream channel wall is curved in sections or over its entire length. The upstream channel wall may in one embodiment in sections or over its entire Have length one, at least substantially, constant radius of curvature or at least substantially constant curvature. In another embodiment, a curvature of the upstream channel wall in sections or over its entire length increase or decrease or decrease or increase their radius of curvature.

If p (x) denotes a radial coordinate of a channel wall, in particular its radially innermost extent or its radially innermost point, at an axial position x, then in one embodiment the channel wall closes at this axial position x with the axis of rotation the angle φ = arctan ( dp / dx). In other words, the angle of a channel wall with the axis of rotation in one embodiment is understood to mean the angle of a tangent to the channel wall with the axis of rotation.

According to the second angle in the direction of flow increases more than the first angle. In particular, therefore, the upstream channel wall sections or over its entire length be more curved than the downstream channel wall, so that the Abblaskanal diverges in one embodiment in sections or over its entire length.

In one embodiment, the exhaust duct runs in sections or over its entire length from the radially outer wall of the annular space radially outward or away from the axis of rotation. Accordingly, in one embodiment, the first and / or second angle increasing in the flow direction from the axis of rotation to the downstream or upstream channel wall is always greater than zero. If, in one embodiment, the radially outer wall of the annular space converges in the direction of flow, the first and / or second angle may be negative in a development on the radially outer wall of the annular space and positive in the direction of flow.

The upstream channel wall, in one embodiment, transitions downstream from a trailing edge of the guide grid into the annulus. In another embodiment, the upstream channel wall transitions upstream from a trailing edge of the guide grid into the annulus. In other words, the blow-off channel is in this other one

Execution partially arranged in the guide grid or the trailing edge of the guide grid axially within the Abblaskanals.

According to one aspect of the present invention, a trailing edge of one or more, preferably all, vanes of the guide grid over the entire Schaufelblatt- or annulus height or at least in a radially outer or Abblaskanalnäheren third, preferably a radially outer fifth or the radially outer 20% a Leitgitter- or Leitschaufelblatthöhe, in particular the radially outer 15% of the Leitgitterhöhe inclined in the circumferential direction to a suction side of the guide vane. In one embodiment, the trailing edge is monotonically, in particular strictly monotone, increasingly inclined to the suction side. In other words, in one embodiment, the trailing edge is bent at least in the radially outer 20%, in particular 15%, the Leitgitter- or Leitschaufelblattthöhe in the circumferential direction to the suction side. This bending can be done in one embodiment by rotating the entire stator blade profile or by changing the blade curvature in the trailing edge region.

Additionally or alternatively, in one embodiment, the trailing edge over the entire blade height or at least in the radially outer third, preferably in the radially outer 20%, in particular 15% of Leitgitterelblattthegel relative to a radially innermost Hinterkantennabenpunkt this outer region axially upstream or be offset towards the front edge. In other words, the vane (s), at least in a radially outer region or the vicinity of the Abblaskanals be shortened.

Additionally or alternatively, in one embodiment, the trailing edge may include an angle with the upstream channel wall that is between 60 ° and 120 °, in particular between 75 ° and 105 °, measured in the axial direction or with respect to the projection in the meridian plane.

By one or more, preferably all the above-mentioned features of the trailing edge (s) of the guide grid, in one embodiment, the tapped flow can be performed with even less loss. Additionally or alternatively, losses of the main flow in the annular space downstream of the leading edge can thereby be further reduced.

insbesondere $$\mathrm{0,4}\cdot \left({\mathrm{m}}_{\mathrm{Bleed}}/{\mathrm{m}}_{\mathrm{in}}\right)\cdot \left({\mathrm{R}}^2-{\mathrm{r}}^2\right)/\mathrm{R}\le {\mathrm{b}}_1,$$

und/oder $${\mathrm{b}}_1\le \mathrm{0,7}\cdot \left({\mathrm{m}}_{\mathrm{Bleed}}/{\mathrm{m}}_{\mathrm{in}}\right)\cdot \left({\mathrm{R}}^2-{\mathrm{r}}^2\right)/\mathrm{R},$$

insbesondere $${\mathrm{b}}_1\le \mathrm{0,6}\cdot \left({\mathrm{m}}_{\mathrm{Bleed}}/{\mathrm{m}}_{\mathrm{in}}\right)\cdot \left({\mathrm{R}}^2-{\mathrm{r}}^2\right)/\mathrm{R}$$

mit:

b₁:

Kanalhöhe an der Eintrittskante, insbesondere Abstand bzw. kürzeste Strecke zwischen Eintrittskante und stromaufwärtiger Kanalwand;

m_Bleed:

Massenstrom im Abblaskanal;

m_in:

Massenstrom im Leitgitterzulauf;

R:

Außenradius des Ringraums, insbesondere am Übergang der stromaufwärtigen Kanalwand in die radial äußere Wand des Ringraums; und

r:

Innenradius des Ringraums, insbesondere am Übergang der stromaufwärtigen Kanalwand in die radial äußere Wand des Ringraums.

In one embodiment: $$0.3\cdot \left({\mathrm{m}}_{\mathrm{Bleed}}/{\mathrm{m}}_{\mathrm{in}}\right)\cdot \left({\mathrm{R}}^2-{\mathrm{<figure-callout\; id="2"\; label="r"\; filenames="imgf0001.png,imgf0002.png"\; state="\{\{state\}\}">r</figure-callout>}}^2\right)/\mathrm{R}\le {\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1.$$

especially $$0.4\cdot \left({\mathrm{m}}_{\mathrm{Bleed}}/{\mathrm{m}}_{\mathrm{in}}\right)\cdot \left({\mathrm{R}}^2-{\mathrm{<figure-callout\; id="2"\; label="r"\; filenames="imgf0001.png,imgf0002.png"\; state="\{\{state\}\}">r</figure-callout>}}^2\right)/\mathrm{R}\le {\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1.$$

and or $${\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1\le 0.7\cdot \left({\mathrm{m}}_{\mathrm{Bleed}}/{\mathrm{m}}_{\mathrm{in}}\right)\cdot \left({\mathrm{R}}^2-{\mathrm{<figure-callout\; id="2"\; label="r"\; filenames="imgf0001.png,imgf0002.png"\; state="\{\{state\}\}">r</figure-callout>}}^2\right)/\mathrm{R}.$$

especially $${\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1\le 0.6\cdot \left({\mathrm{m}}_{\mathrm{Bleed}}/{\mathrm{m}}_{\mathrm{in}}\right)\cdot \left({\mathrm{R}}^2-{\mathrm{<figure-callout\; id="2"\; label="r"\; filenames="imgf0001.png,imgf0002.png"\; state="\{\{state\}\}">r</figure-callout>}}^2\right)/\mathrm{R}$$

With:

b ₁ :

Channel height at the leading edge, in particular distance or shortest distance between the leading edge and the upstream channel wall;

m _bleed :

Mass flow in the exhaust duct;

m _in :

Mass flow in the Leitgitterzulauf;

R:

Outer radius of the annular space, in particular at the transition of the upstream channel wall in the radially outer wall of the annular space; and

r:

Inner radius of the annular space, in particular at the transition of the upstream channel wall in the radially outer wall of the annular space.

insbesondere $${\mathrm{b}}_1\le {\mathrm{r}}_{\mathrm{K}}/\mathrm{4,}$$

mit:

r_K:

Krümmungsradius der stromaufwärtigen Kanalwand, insbesondere am Übergang der stromaufwärtigen Kanalwand in die radial äußere Wand des Ringraums oder an der Eintrittskante.

Additionally or alternatively, in one embodiment: $${\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1\le {\mathrm{r}}_{\mathrm{K}}/\mathrm{5,}$$

especially $${\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1\le {\mathrm{r}}_{\mathrm{K}}/\mathrm{4,}$$

With:

r _K :

Radius of curvature of the upstream channel wall, in particular at the transition of the upstream channel wall in the radially outer wall of the annular space or at the leading edge.

insbesondere $$\mathrm{0,9}\cdot {\left[{\left({\mathrm{r}}_{\mathrm{K}}+{\mathrm{b}}_1\right)}^2-{\left({\mathrm{r}}_{\mathrm{K}}+\mathrm{H}\right)}^2\right]}^{1/2}\le \mathrm{L},$$

und/oder $$\mathrm{L}\le \mathrm{1,5}\cdot {\left[{\left({\mathrm{r}}_{\mathrm{K}}+{\mathrm{b}}_1\right)}^2-{\left({\mathrm{r}}_{\mathrm{K}}+\mathrm{H}\right)}^2\right]}^{1/2},$$

insbesondere $$\mathrm{L}\le \mathrm{1,1}\cdot {\left[{\left({\mathrm{r}}_{\mathrm{K}}+{\mathrm{b}}_1\right)}^2-{\left({\mathrm{r}}_{\mathrm{K}}+\mathrm{H}\right)}^2\right]}^{1/2}$$

mit:

H:

radialer Abstand zwischen der Eintrittskante und dem Übergang des Ringraums in die stromaufwärtige Kanalwand; und

L:

axialer Abstand zwischen der Eintrittskante und dem Übergang des Ringraums in die stromaufwärtige Kanalwand; und

r_K:

lokaler Krümmungsradius, insbesondere bei b₁.

Additionally or alternatively, in one embodiment: $$0.5\cdot {\left[{\left({\mathrm{r}}_{\mathrm{K}}+{\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1\right)}^2-{\left({\mathrm{r}}_{\mathrm{K}}+\mathrm{<figure-callout\; id="2"\; label="H"\; filenames="imgf0001.png,imgf0002.png"\; state="\{\{state\}\}">H</figure-callout>}\right)}^2\right]}^{1/2}\le \mathrm{L}.$$

especially $$0.9\cdot {\left[{\left({\mathrm{r}}_{\mathrm{K}}+{\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1\right)}^2-{\left({\mathrm{r}}_{\mathrm{K}}+\mathrm{<figure-callout\; id="2"\; label="H"\; filenames="imgf0001.png,imgf0002.png"\; state="\{\{state\}\}">H</figure-callout>}\right)}^2\right]}^{1/2}\le \mathrm{L}.$$

and or $$\mathrm{L}\le 1.5\cdot {\left[{\left({\mathrm{r}}_{\mathrm{K}}+{\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1\right)}^2-{\left({\mathrm{r}}_{\mathrm{K}}+\mathrm{<figure-callout\; id="2"\; label="H"\; filenames="imgf0001.png,imgf0002.png"\; state="\{\{state\}\}">H</figure-callout>}\right)}^2\right]}^{1/2}.$$

especially $$\mathrm{L}\le 1.1\cdot {\left[{\left({\mathrm{r}}_{\mathrm{K}}+{\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1\right)}^2-{\left({\mathrm{r}}_{\mathrm{K}}+\mathrm{<figure-callout\; id="2"\; label="H"\; filenames="imgf0001.png,imgf0002.png"\; state="\{\{state\}\}">H</figure-callout>}\right)}^2\right]}^{1/2}$$

With:

H:

radial distance between the leading edge and the transition of the annulus into the upstream channel wall; and

L:

axial distance between the leading edge and the transition of the annulus into the upstream channel wall; and

r _K :

local radius of curvature, especially at b ₁ .

insbesondere $${\mathrm{b}}_1\ge \mathrm{0,7}\cdot {\mathrm{b}}_2,$$

mit:

b₂:

Austrittskanalhöhe an dem Abblaskanalaustritt, insbesondere Abstand bzw. kürzeste Strecke zwischen ringraumabgewandtem Ende der stromaufwärtigen Kanalwand und stromabwärtigen Kanalwand.

Additionally or alternatively, in one embodiment: $${\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1\ge 0.5\cdot {\mathrm{<figure-callout\; id="2"\; label="b"\; filenames="imgf0001.png,imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_2.$$

especially $${\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1\ge 0.7\cdot {\mathrm{<figure-callout\; id="2"\; label="b"\; filenames="imgf0001.png,imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_2.$$

With:

b ₂ :

Outlet channel height at the Abblaskanalaustritt, in particular distance or shortest distance between annularraumabgewandtem end of the upstream channel wall and the downstream channel wall.

insbesondere $$\left({\mathrm{b}}_2-{\mathrm{b}}_1\right)/\mathrm{s}\le \mathrm{0,14,}$$

mit:

s:

Länge der stromabwärtigen Kanalwand zwischen der Eintrittskante und dem Abblaskanalaustritt.

Additionally or alternatively, in one embodiment: $$\left({\mathrm{b}}_2-{\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1\right)/\mathrm{s}\le 0.2$$

especially $$\left({\mathrm{b}}_2-{\mathrm{<figure-callout\; id="1"\; label="b"\; filenames="imgf0002.png"\; state="\{\{state\}\}">b</figure-callout>}}_1\right)/\mathrm{s}\le 0.14$$

With:

s:

Length of the downstream channel wall between the leading edge and the exhaust channel exit.

Each of the above provisions (1) - (7 ') already yields per se, in particular in combination with one or more, in particular all the other regulations a particularly advantageous Abblaskanal. In one embodiment, b ₁ is first determined according to at least one of the equations (1) - (2 '), and in a further development, further variables, in particular r _K , H, L, b ₂ and / or s, according to one of the equations (3 ) - (7 ') derived.

Fig. 1:

einen Teil eines Gasturbinenverdichters einer Flugtriebwerk-Gasturbine nach einer Ausführung der vorliegenden Erfindung in einem Meridianschnitt;

Fig. 2:

einen Teil eines Gasturbinenverdichters einer Flugtriebwerk-Gasturbine nach einer weiteren Ausführung der vorliegenden Erfindung in einem Meridianschnitt;

Fig. 3:

einen vergrößerten Ausschnitt der Fig. 1; und

Fig. 4:

eine Sicht auf eine Hinterkante des Leitgitters des Gasturbinenverdichters der Fig. 1 entgegen der Durchströmungsrichtung.

Further advantageous developments of the present invention will become apparent from the dependent claims and the following description of preferred embodiments. This shows, partially schematized:

Fig. 1:

a portion of a gas turbine compressor of an aircraft engine gas turbine according to an embodiment of the present invention in a meridian section;

Fig. 2:

a portion of a gas turbine compressor of an aircraft engine gas turbine according to a further embodiment of the present invention in a meridian section;

3:

an enlarged section of the Fig. 1 ; and

4:

a view of a trailing edge of the guide grid of the gas turbine compressor of Fig. 1 against the direction of flow.

Fig. 1 shows a portion of a gas turbine compressor of an aircraft engine gas turbine according to an embodiment of the present invention in a meridian section. This has a guide grid with a plurality of circumferentially distributed guide vanes 1 and a playpen with a plurality of circumferentially distributed blades 2.

The guide grid is arranged upstream of the downstream walkway and a further, in particular in the flow direction x last exit guide grille (not shown). One or more further running and guide gratings may be arranged between the illustrated guide grid and the outlet guide grid (not shown).

Guiding and playpens are arranged in an annular space 5, which is intended to be flowed through during operation of compressed air.

A radially outer wall (top in Fig. 1 ) of the annular space is at a transition 4 continuously or without offset in an upstream channel wall 3.1 of a Abblaskanals 3 via. Axially opposite the Abblaskanal a downstream channel wall 3.2 with a radially inner, rounded leading edge 3.3, which is offset from the transition 4 radially inward. At an end remote from the annular space (at the top in FIG Fig. 1 ) has the Abblaskanal 3 a Abblaskanalaustritt.

The Abblaskanal communicates at its Abblaskanalaustritt with a plenum (not shown). Likewise, it can also communicate with an inflow channel, which in turn can communicate with the plenum.

The downstream channel wall 3.2 closes with a rotational axis of the compressor (horizontal in Fig. 1 ) a strictly monotonically increasing in the flow direction x from the leading edge 3.3 first angle α, in other words is curved over its entire length (dα / dx> 0).

The upstream channel wall 3.1 includes with the axis of rotation in the flow direction from the transition 4 strictly monotonically increasing second angle β, is with In other words, also curved over its entire length (dβ / dx> 0), wherein the upstream channel wall merges tangentially into the radially outer wall of the annular space 5.

The upstream channel wall is in the execution of Fig. 1 downstream (right) of the trailing edges 1.1 of the guide vanes of the guide grid 1 in the radially outer wall of the annular space 5 via.

Fig. 4 shows a view of a trailing edge 1.1 of a guide vane of the guide grid 1 against the flow direction (ie from the right in Fig. 1 ).

As can be seen in particular from this, the trailing edges 1.1 are at least in the radially outer 20%, in particular 15% of Leitgitter- or Leitschaufelblatthöhe (Rr) (see. Fig. 1 ) in the circumferential direction from a pressure side PS away to a suction side SS of the guide blade toward strictly monotonically increasingly inclined, in other words bent to the suction side SS.

Fig. 3 shows in an enlarged section of the Fig. 1 in particular the blow-off duct with several sizes. In this case, b ₁ denotes the channel height at the leading edge 3.3, in particular the distance or the shortest distance between the leading edge 3.3 and upstream channel wall 3.1, R or r the outer or inner radius of the annular space at the transition 4 of the upstream channel wall 3.1 in the radially outer Wall of the annular space 5 (see. Fig. 1 ), R _K denotes the radius of curvature of the upstream channel wall 3.1, H is the radial distance between the leading edge 3.3 and the junction 4 of the annular space 5 in the upstream channel wall 3.1, L is the axial distance between the leading edge 3.3 and the junction 4 of the annular space 5 in the upstream Channel wall 3.1, b _2, the outlet channel height at the Abblaskanalaustritt and s the length of the downstream channel wall 3.2 between the leading edge 3.3 and the Abblaskanalaustritt.

Fig. 2 shows in Fig. 1 Similarly, a portion of a gas turbine compressor of an aircraft engine gas turbine according to an embodiment of the present invention. Corresponding features are denoted by identical reference numerals, so that the description of the embodiment of Fig. 1 Referred to below and will be discussed only for differences to this.

In the execution of Fig. 2 the upstream channel wall 3.1 goes upstream (left) from the trailing edge 1.1 of the guide grid in the radially outer wall of the annular space 5, the axially upstream upstream of the leading edge 3.3 is arranged. In other words, the exhaust duct 3 in the embodiment of Fig. 2 partially arranged in the guide grid.

Although exemplary embodiments have been explained in the foregoing description, it should be understood that a variety of modifications are possible. It should also be noted that the exemplary embodiments are merely examples that are not intended to limit the scope, applications and construction in any way. Rather, the expert is given by the preceding description, a guide for the implementation of at least one exemplary embodiment, with various changes, in particular with regard to the function and arrangement of the components described, can be made without departing from the scope, as it turns out the claims.

LIST OF REFERENCE NUMBERS

1

Vane / grids

1.1

trailing edge

2

Blade / grids

3

exhaust duct

3.1

upstream channel wall

3.2

downstream channel wall

3.3

leading edge

4

Transition to the upstream channel wall

5

annulus

Claims (8)

1. Gas turbine compressor comprising a guide vane (1), an in particular downstream moving vane (2) and a bleed channel (3), which comprises an upstream channel wall (3.1) that transitions into an annular chamber (5), an axially opposite downstream channel wall (3.2) comprising an in particular rounded inlet edge (3.3), and a bleed channel outlet,
   the upstream channel wall and a rotational axis of the compressor forming, in the meridian section, a first angle (α) that increases in the direction of flow (x); and
   the upstream channel wall and the rotational axis forming, in the meridian section, a second angle (β) that increases in the direction of flow
   characterized in that
   the upstream channel wall is arranged upstream of a trailing edge (1.1) of the guide vane; and
   the second angle increases more in the direction of flow than the first angle.
2. Gas turbine compressor according to the preceding claim, characterized in that the first angle increases from the inlet edge and/or monotonically, in particular strictly monotonically.
3. Gas turbine compressor according to either of the preceding claims, characterized in that the first angle at the bleed channel outlet is larger than 30°.
4. Gas turbine compressor according to any of the preceding claims, characterized in that the second angle increases monotonically in the direction of flow.
5. Gas turbine compressor according to any of the preceding claims, characterized in that the upstream channel wall transitions into the annular space upstream or downstream of the trailing edge (1.1) of the guide vane.
6. Gas turbine compressor according to any of the preceding claims, characterized in that a trailing edge (1.1) of at least one guide blade of the guide vane is inclined, at least at a radially outer third of a guide vane height, in particular monotonically increasing, to a suction side of the guide blade in the peripheral direction and/or is offset axially upstream and/or forms, together with the upstream channel wall, an angle that is between 60 ° and 120 °.
7. Gas turbine compressor according to any of the preceding claims, characterized in that 0.3 · (m_Bleed/m_in) · (R² - r²)/R ≤ b₁ ≤ 0.7 · (m_Bleed/m_in) · (R² - r²)/R; and/or
   b₁ ≤ r_K/5; and/or $$0.8\cdot {\left[{\left({\mathrm{r}}_{\mathrm{K}}+{\mathrm{b}}_1\right)}^2-{\left({\mathrm{r}}_{\mathrm{K}}+\mathrm{H}\right)}^2\right]}^{1/2}\le \mathrm{L}\le 1.2\cdot {\left[{\left({\mathrm{r}}_{\mathrm{K}}+{\mathrm{b}}_1\right)}^2-{\left({\mathrm{r}}_{\mathrm{K}}+\mathrm{H}\right)}^2\right]}^{1/2};$$

   

   and/or $${\mathrm{b}}_1\le 0.5\cdot {\mathrm{b}}_2;$$

   

   and/or $$\left({\mathrm{b}}_2-{\mathrm{b}}_1\right)/\mathrm{s}\le 0.2$$

   

   applies, in which b₁ is the inlet channel height on the inlet edge, m_in is the mass flow rate in the guide vane intake, m_Bleed is the mass flow rate in the bleed channel, R is the outer radius of the annular space, r is the inner radius of the annular space, r_K is the radius of curvature of the upstream channel wall, H is the radial spacing between the inlet edge and the transition of the annular space into the upstream channel wall, L is the axial spacing between the inlet edge and the transition of the annular space into the upstream channel wall, b₂ is the outlet channel height at the bleed channel outlet and s is the length of the downstream channel wall between the inlet edge and the bleed channel outlet.
8. Gas turbine, in particular an aircraft engine gas turbine, characterized by a gas turbine compressor according to any of the preceding claims.

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